0.05: 90: 00
9'2s: TO: 00
8.20: so: 00
9'EZ: Lo: 00
E -0s: so: 00
T's9:zO:00
T0:OO:ET
008 6T I
09C 05 00:OO:ST
009 2Z ZLL 62
t-
Launch Vehicle configurat ion I Flight durat ion
Complex Wasion Time, C.m.t.. Date I hr:min:sec I Launch vehic le I Spacecraf t
~~
bAS-201 Spacecraft and launch vehic le development, suborb i ta l
Feb. 26, 1966 16: 12 :01 Saturn I B (SA-201)
Modified Block I con- mand and serv ice mod- ule , adapter and launch escape system I sc-009)
OO:37 : 19.7 A.F. Eastern 34 Test Range
I A.F. Eastern 378 T e s t Range I Ju ly 5, 1966 Saturn I B with
nose cone (SA-203)
AS-203 Launch vehicle devel- opment, e a r t h or- b i t a l
14:53:17
I
01 :33 :02 AS-202 Spacecraf t and launch vehic le development, nuborbi ta l
Aug. 25. 1966 Saturn I B (SA-2 02 )
Block I colmnand and serv ice module, adapter , and launch e h a p e system (SC-011)
1 7 : 55: 32 A.F. Eastern 34 Test Range
Kennedy 39A Space Center
A.F. Eastern 37B Teat Range
Kennedy 39A Space Center
Saturn V (SA-5 01)
Block I coormand and service module, adapter , and launch escape system (SC-017). and lunar module test a r t i c l e
08: 37 : 09.2 dApollo 4
A Nov. 9, 1967 12: 00: 01
07:52: 10 eApollo 5
B 22 : 48 : 08 Saturn IB (SA-204)
m d i f i e d lunar m d u l e (LM-1). adapter. and nose cone
Jan. 22, 1961
Block I cormand and serv ice module. adapter and launch
09:57:19.9 12:OO:Ol Saturn V Apr. 4. 1968 (SA-502
gApollo 6
A
I escape system (SC-020). and lunar module t e a t I
%laaim typea A and B are defined in t a b l e %I.
b I n i t i a l f l i g h t of Saturn LB launch vehicle.
'S-fVB stage destroyed a f t e r four revolutions.
d I n i t i a l f l i g h t of Saturn V launch vehicle .
e I n i t i a l f l i g h t of lunar mdule. f F i n a l communication u i t h ascent s tage p r i o r t o impact.
'S-IVB f a i l e d t o restart at end of second revolution.
Spacecraft boosted t o apogee of 9769 miles a f t e r two revolut ions t o s imulate lunar- re turn en t ry conditions.
Spacecraft propulsion used to achieve 12 020-mile apogee t o simulate lunar- re turn e n t r y conditiona.
A-5
l i r h t d u r a t i o br:min:.ec
Launch d a t a I V*hiclaB
Block I1 c& Apollo 7 .Id U r v i C . d-
adapter . mud h u n c h uup. ayrtem
u l a (CSn401).
260: 09: 03 k h i r r a
Backup: S taf ford
Block I1 c o v n d and r r v i c e l d u l e (CW-103). d a p t e t , launch amcape my#- tu, and l u n a r v d . ule talc a r t i c l e
12:Sl:W 1ILturn V (SA-503)
A p l l o 8 l47:W :42
Loval l hders
Amstmnp Aldr in
Backup:
H c D i v l t t Scot t S c h n i c h r t
Backup: Conrsd Cordon
241 : M: 54 (SA-504)
(SA-505)
(Csn-104). 1-r .Odula (u4-31, adapter . mud h u n c h -up. 17rta
Block 11 c o v a d and nice v d u l e
v d u l . (Iw-4). adaptar , md launcl
(Csn-106). 1-r
mscapc mystem
192:OJ: 23 F prime: Staf ford YOUnp C.IP*n
Backup: Cooper Lisele Mitchel l
Block I1 c-nd and r r v i c a v d u l a (CSW-107). l u n a r l d u l e ( w - 5 ) . adapter . m d launct e s c s p . aystem
195: 18: 35 G P r h : Anarronp Collin. Aldr in
Lov.11 Anderr b l a e
Uckup: I
246 :36:25 16:22:M Saturn V (SA-507) I
19:13:W %turn V (SA-508)
21:03:02 Ssturn V t (SA-509)
Block I1 c-nd .ad service d u h (CSlI-109), 1-T d u l . (In-7). sdsptar . and l sunc l sacape myylfU
142:54:41
216:01:58 : s w u t t y
J t h t a r e a ilNk
Block I1 c- Md w n l c s v d u l e (csI-112), l w r d u l R ( I w - l O ) , s d a p r i r and lsunch racape m y s t n
259:U:53 13: 34: W Sltllrn v (SA-510) spc. calter
I
A-6
TABLE A - N . - APOW/SATURN RIGHTS - Concluded
)Liaaion
Apollo 16
Apollo 17
P r h :
Backup:
Prim: banady space Custer
S c N t t Backup:
h e . C.U.L. h r : a i n : r c
17 : 54 : W
OS : 33: W
h u n c h vehicle
saturn v (SA-511)
Vehicles
Ducript ion
c__
Block I1 c o w a d and aewice mdule (csn-113). lunar module (U4-11). adapter and launch ..cape symre.
‘ rumion t)pea defined in tabla bI. b C r n n a are l i e r e d in order o f C o u n d a r . C o l u n d Wd* Pilot. &d Lmdr nodule P f l o t . CSpac*craft assi8n.d for i d m t i f i c a t i o n radio cmmunication. %asion aborted prior ca scheduled l u m r l m d i n g . %.ckup cr- srlgerc raplacad p r i m c r m n II.tcin&ly 2 days b f o r . hunch.
l i s h t duration h r : a o : aec
265 : 51 :05
4
.
.-- __ _ _ _ _ .. .. . . . . - . . ..
.. L
Apollo 11
Apollo 12
Apollo 14
Apollo 15
Apollo 16
Apollo 17
Armstronl Aldrin
Conrad Be-
Shepard Mitchell
S c o t t 1-n
y-8 Dub
Cernrn Schmitt
Are8
Sea of rranquility
Ocean of stoma
Fra Muro
bdley- Apemine
Taurun- Littrow
a t i t u d r
0.7.N -
3.2.S
3.6.S
26.l.N
9.09
20.2.N
Landing
Longitude
23.4.E
23.4%
17.5%
3.7.E
15.5.E
30. 8'E
TmLE A-V.- LUNAR SURFACE OPERATIOllS
t a
Date
July 20, 196
Nov. 19. 196
Feb. 5. 1971
July 30, 191
Apr. 21, 191
Dac. 11. 191
iae, G.m.t. . hr :min: nec
20: 17: 40
06:54:36
09 : 18 :11
22 : 16:29
02: 23: 35
19:54:57
c *
Extravehicular a c t i v i t y
Traverse vehicle
None
time
bdular aquipment transporter
LRV-1
LRV-2
LRV-3
Distance troveled. km
Sl
Pirat: %l Second: 1.3 r0t.i: a . 3
Firs t : ?.1 Second: 3.0
rotal: 14.0
F i r n t : 10.3 Second: 12.5 Third: 5.1 rotal : 27.9
Firs t : 4.2 second: 11.1 Third: 11.4 Total: 26.7
Firnt: 3.3 second: 18.9 T h i r d : 11.6 Total: 33.8
Duration, hr:nin:sec
bo2:31:40
Firnt: 03:56:03 Second: 03:49:15 %td: 07:45:ia
Fi r s t : W:47:50 Second: 04:34:41 %td: 09:22:31
Stmdup: 00:33:07 Fi r s t : 06:32:42 Second: 07:12:14 Third: W:49:50
5ot.l: 19:07:53
Firat : 07:11:02 Second: 07:23:11 Third: 05:40:03
dTotd : 20:14:16
Fi r s t : 07:11:53 Second: 07:36:56 Third: 07:15:08
dTotd : 22:03:57
21.0
Firnt : 16.7 Sacond: 17.6 Total: 34.3
Firnt: 20.5 Second: 22.3 Total: 42.8
Firnt: 14.5 second: 34.9 Third: 27.3 Total: 76.7
Firat: 29.9 Second: 29.0 Third: 35.4 Totml: 94.3
F i r s t : 14.3 Second: 34.1 Third: 62.0 Total: 110.4
Lurface ntay time.
hr:min:sec
21: 36:21
31: 31:12
33: 30: 31
66: 54 : 53
71 I 02 : 13
74:59:40
*Cr- listed in order of Col.nder and Lunar W u l e Pilot.
bh.ed upon t i m e n of hatch openlag and closing. upon ti- of egrans and ingraas.
dEa.ad upon t i m a at vhich cabin prennure reachad 3.0 poi during depreeauriration and repreanurization.
I
,
I
I
A-8
TABLE A-V1.- MANNED ORBITAL OPERATIONS AND INFLIGHT EXTRAWIm ACTIVITY
Coamrand Nodule P i l o t s o l o opera t ions f i r t h 171 Earth o r b i t a l
L u n a r ill hr:min hr:min:sec
revolut ions Transearth extrave- revolutions hfcu lar a c t i v i t y . Crewmen Duration,
revolut ions
Apollo 9 151 Scot t ‘1 : 01 - Schweickart 1:07
Apollo 10 ‘1 - - 31
Apollo 11 1 - I 30 -
Apollo 12 ‘1 - - 45
Apollo 14 ‘1 - - 34
- - - Apollo 13 ‘1
l A p o 1 1 0 1 5 - = 1 I - I - I 74 --- Apollo 16 ‘1 I I 64
Apollo 17 dl - - 75
Worden
Matt ingly
Evans
I - I I
- - I
-1 00: 39:07
-~ ~~
40 01:23:42
39 01: 05 : 44 - ‘Crewmen l i s t e d in order of Command NDdule P i l o t and Lunar Module P i l o t .
bExtravehicular a c t i v i t y t i m e based upon times a t which cabin pressure reached 3.0 p s i during
%ransluuar i n j e c t i o n performed over P a c i f i c Ocean before completion of second revolut ion.
dTranslunar i n j e c t i o n p e r f o r w d over At lan t ic Ocean.
‘Extravehicular a c t i v i t y durat ions shown are based upon times a t vhich cabin pressure reached 3.0 ps i
depressurizat ion and repressurizat ion.
during depressurizat ion and repressurizat ion. Durations based on o t h e r events a r e a s follows.
(1) (2) Egress t o ingram: LMp - 47 min 3 sec. (3)
Hatch open t o hatch closed: CW - 47 min. LMP - 1 h r 1 mfa.
Arrive a t and leave EVA s ta t ion : LMP - 37 min.
.
Distance from Longitude target, mi. Comnand module
f l o t a t i o n a t t i t u d e (a) (a)
TABLE A-VI1.- RECOVERY DATA
T h e required for U.S.S. upright ing, min recovery ahig
I
AS-201
AS-20'2
Apollo 4
Apollo 6
~~
Feb. 26. 1966 16:49:20
Aug. 25. 1966 18:48:34
Nov. 9. 1967 20:37:10
Apr. 4, 1968 21:57:21
Apollo 7
Apollo 8
Apollo 9
Apollo 10
Apollo 11
Apollo 12
Apollo 13
Apollo 14
Apollo 15
Apollo 16
Apollo 17
Landinn d a t a I I
~ ~~
Oct. 22, 1968 11:11:48
Dcc. 27. 1968 15:51:42
Mar. 13. 1969 17:00:53
Hay 26, 1969 16:52:23
J u l . 24. 1969 16:50:35
Nov. 24, 1969 20:58:25
Apr. 17, 1970 18:07:41
Feb. 9 , 1971 22:05:00
Aug. 7. 1971 20:45:53
Apr. 27, 1972 19:45:05
Dec. 19. 1972 19:24:59
Ltlantic
' ac i f ic
i t l n n t i c
' ac i f ic
'acific
' ac i f ic
' ac i f ic
t 'acif ic
Pnc i f i c
Paci f ic
Pac i f ic
Unmanned Missions
Upright
Upright
Upright
27'38'N
8'06"
'23'13'N
15'04's
13'18'N
15O47'S
21'38's
27*01'S
26°08'N
0'42's
17'53's
Hanned Missions
64'09'U
165'01'W
67"59'W
164'39'W
169"09'W
165'09'W
165'22'W
1 7 2'40' W
158'08 'W
156*13'W
166'07'W
1.9
1.4
2.7
1.3
1 .7
2.0
1.0
0.6
1.0
3.0
1.0
Inverted
Inverted
Upright
Upright
Inverted
Inverted
Upright
Upright
Upright
Inverted
Upright
c12
6.0
- - 7.6
4.5
- - - 4.5
I
Boxer
Hornet
Banning ton
Oklnawa
Esaex
Yorktovn
Cuadalcnnal
Princeton
Home t
tbrne t
Iw J h
New Orleana
Olrinawa
Ticonderogs
Ticonderoga
'The coordinatas shown are the beat estimate of the actual comaand d u l e landing point and m y be bnaed upon recovery s h i p p o s i t i o n
bCoarmsnd module was upright when eighted; however, l o s s of VHF recovery bencon f o r a period of 2 mlnutea indicnted that the command
data , cormaand d u l e computer da ta , o r t r a j e c t o r y reconstruct ion.
module had probably been inver ted prior t o s ight ing.
/-
'Uprighting bag inflation uaa not i n i t i a t e d u n t i l approximately 8 minutea after landing.
,
.
I
.
B-1
APPENDIX B - APOLLO MISSION TYPE DESIGNATIONS
B-2
TABLE B-I .- MOLL0 MISSION TYPE DESIGIJATIOITS
Mission assignment
Apollo 4 Apollo 6
Apollo 5
Apollo 7
Apollo 8
Apollo 9
Apollo 10
Apollo 11 -
Apollo 12 Apollo 13 Apollo 14
Apollo 15 Apollo 16 Apollo 17
Trajectory Purpose
Earth orbital Launch vehicle and spacecraft development.
Earth orbital Lunar module unmanned flight evaluation.
Earth orbital Comnd and service module manned flight denonstration.
Lunar orbital Command and service module manned flight demonstration.
Earth orbital Lunar module manned flight demonstration.
Earth orbital Lunar module manned flight demonstration, augmenting mission type D objectives. I
Lunar orbital Lunar mdule manned flight demonstration.
Lunar landing Manned lunar landing demonstration.
Lunar landing Precision manned lunar landing demonstra- tion and systematic lunar exploration.
Lunar landing Extensive scientific investigation of moon on lunar surface and fron lunar orbit. I
4
c-1
.
APPENDIX C - APOLLO SPACECRAFT WEIGHTS
I
Mission phase/aasembly
Spacecraf t a t launch:
bCommaad and eerv ice modules
bLunar w d u l e o r test article
Spacecraf t l lunar module adapter
Launch escape system
T o t a l weight:
bCommand module at e n t r y in te r face
bColrmrand module a t landing
a A l l values i n pounds.
TABLE C-I.- AF'OUO SPACECRAFT WEIGHTSa (Unmanned F l i g h t s )
CSM-002 A404
c
CSM-009 AS-201
33 805
-
3 691
8 334
45 830
-
(C 1
Spacecraftfmission
CSM-011 As-202
44 385
- 3 725
8 611
56 721
- (C)
CSM-017lLTA-1OR Apollo 4
51 591
29 500
3 880
8 710
, 93 681
' 11 949
1 10 540
bPropel lants and o t h e r expendables included.
'Data not ava i lab le .
dAdapter was considered p a r t of launch vehicle .
eBased on measured weights a t launch.
LM-1 Apollo 5
- 31 528
(d)
- 31 528
- -
:SM-02O/LTA-2R Apollo 6
55 420
26 001
3 886
8 886
94 193
12 508
11 260
,,.-
TABLE C-I.- APOLLO SPACECRAFT WEIGHTSa - Continued
(Apollo 7 through Apollo 12)
.Spacecraft/mission
Mission phaselassembly ~~~ ~
CSM-104lLM-3 Apollo 9
CSM-106lLM-4 Apollo 10
CSM-107lLM-5 Apollo 11
CSM-108/ LM-6 Apollo 12
C SM-103 / LTA-B Apollo 8
CSM-101 Apollo 7
Spacecraft a t launch:
Connuand and s e r v i c e modules
Lunar m d u l e o r test a r t i c l e
Spacecraf t l lunar module
Launch escape system
Total :
adapter
32 586 -
3 852
8 874
45 312
63 531
19 900 3 951
8 890
96 272
59 086
32 132
4 012
8 869
104 099
63 567
30 735
3 970
8 934
107 206
63 508
33 297
3 951
8 910
109 666
63 578
33 587
3 962
8 963
110 090
Spacecraf t a f t e r lunar o r b i t i n s e r t ion:
Conmaad and s e r v i c e modules
Lunar module
Total :
46 743 -
46 743
38 697
30 732
69 429
38 743
33 295
72 038
38 751
33 584
72 336
Lunar module a t lunar landing:
Ascent s t a g e
Descent s tage
Tota l :
1 0 914
5 239
1 6 153
10 827
5 737
16 564
Lunar module ascent s tage
‘Lunar module ascent s t a g e
a t l u n a r l i f t - o f f
a t j e t t i s o n
Command m d u l e a t e a r t h
Corrmrand m d u l e a t landing
e n t r y i n t e r f a c e
- -
12 356
11 bo9
- -
12 171
10 977
b10 216
d5 616
12 257
11 094
b8 273
d5 243
12 137
10 901
10 777
5 463
12 096
10 873
10 750
5 437
12 277
11 05’0
a A l l values are i n pounds and include propel lan te and o ther expendables.
b A t s taging.
‘Unmanned.
TABLE C-I.- APOLU) SPACECRAFT WEIGHTSa - Concluded
(Apollo 13 through Apollo 17)
:ecraf tlmission
Apollo 15 klbsion phaae/aesembly CSM-109/Lw-7
A D O ~ ~ O 13 CSM-llO/LM-8 Apollo 14
Spacecraft at launch:
Command and serv ice modules
Lunar aDduLe
Spacecraft/luuar module adapter
Launch escape system
Total :
Spacecraft a f t e r lunar o r b i t inaer t ion :
Command and serv ice modules
Lunar module
Total:
63 812
33 502
3 947
8 991
110 252
64 464
33 652
3 967
9 037
111 120
66 955
36 222
3 964
9 108
116 249
67 010 66 953
36 255 36 279
3 961 3 961
9 167 ~ 9 104
116 393 116 297
38 174
33 649
71 823
10 898
5 474
16 372
40 109 41 395 40 264
36 220 36 252 36 276
76 329 77 647 76 540 I
Lunar module a t lunar landing:
Ascent s t a g e
Deecent e tage
Total:
10 960
7 215
18 175
10 958 10 989
7 250 6 819
18 208 17 808
10 780
5 307
10 915
5 325
Lunar module ascent s t a g e at lunar l f f t-of f
bLunar module ascent s tage a t j e t t i s o n
10 958 11 005
5 306 5 277
1 2 361
11 133
12 704
11 481
1 2 953
11 731 13 015 1 3 140
11 995 1 2 120
Command module A t e a r t h entry interface
Command module a t landing
a A l l weights are i n pounds and include propel lants and other expendables.
bUnmanned.
‘The lunar module w a s docked t o the comoand module u n t i l j u s t p r ior to entry. A t that t i m e , the weight of the lunar module ascent and descent s tages was 24 647 lb .
L
D- 1.
. APPENDIX D - MAN’NED SPACE FLIGHT RECORDS ESTABLISHED DURING THE A P O U O PROGRAM
The records listed in tables D-I, D-11, and D-1x1 were obtained from the record dossiers of the National Aeronautic Association. by the Federation Aeronautique Internationale (F.A.I.). must be applied for in advance and must exceed the existing record by 10 percent for a new rec- ord to be established. even though better performances were attained In some cases. for distance in the tables is statute miles.
The presently held records are officially recognized Special conditions are that a record
For these reasons, not all of the Apollo performances were documented, The English unit of measurement
.
L
7 TABLE 0-1.- ABSOLUTE W O ~ RECORDS 10
13
e715:06:57 Love11
I 1 Apollo mission 1 14 15 17
09:12: 27 18: 18:26 d21 : 4 9 : 24 Shepard Scott Cernan
&imm difference in radii of geocentric spheres lncercepted by vehicle. bInclucisa mas of crew. 'Tim? . p o t outaide apacacraft uslng UI autonomows life mupport system.
dConsiata of 17 min 40 KC wing ths aetronaut manewering unit for life support during the Gemini IX-A rdesion and 21 hr 31 min 44 m c
'Record subsequently surpassed by Skylab crew.
T i m begins and ends at crossing of vehicle outline when exiting and entering the spacecraft.
of lunar surface extravehicular activity during the Apollo 17 mission.
TABLE D-11.- WORLD CATEGORY RECORDS - ORBITAL MISSIONS (K-2) WITH WO To FWR ASTRONAUTS
I I I Distance in group flight while linked. km ( m i . )
aIncludea pass of crev.
bWith CSn and LH manned. 'Vehicles must remain vithin 100 kilometers of each other for at least one revolution. dRccord subsequently aurpaesed by Skylab crews. eRecord subsequently surpassed by U . S . S . R . (Soyuz 7 and 8) crews.
.
TABLE D-111.- WORLD CATEGORY RECDROS - LUNAR AM) P W A R Y KISSIONS (K-3) WITH Tw) TO POUR MTRO?WTS
Record Apollo mission
8 10 11 12 14 15 16 1 7 1 'Altitude above su r face of the ear th . km (mi . ) I 377 668.9 I (234 672.5)
bCreatest m a s placed i n t o lunar o r b i t from t h e 31 410 ea r th , kg ( lb ) (69 429)
Duration of lunar mission, hr:min:sec 147:00:42 192:03:23 I I I I
244 : 36 : 25 I I 301:51: 57 I I I 1 I I I
'Duration of s t ay in lunar o r b i t , hr:mln:sec 20:06:48 61:34:39 59:27:50 88:56:01 125:46:50 147:41:13 Col l ins Cordon Plattingly Evans 1 8 257.6 I I (16 153.0) I I (18 208.0)
I I 7 326.9 I I bGre.nceat mas l d e d on the moon. It# (lb) I
bCreatest vlss l i f t e d t o lunar o r b i t from lunar 2 689.2 2 705.9 sur face , kg (lb) (5 928.6) ( 5 % 5 . 6 )
Duration of stay on lunar aurface. hr:ain:oec 2 1 :36 :21 31:31:12 71: 02 : 13 Armstrong Conrad young
Aldrin
dTotal t h e ou t s ide opacecraft f o r a11 c r w men while on lunar surface, h r : r in :aec
dTotal time outs ide #pacecraft f o r one crew- m n while on lunar surface. h r : r in :wc
eDiatance t rave led from spacecraf t while on
02 : 31 :40 Armatrong
lunar surface. I ( f t )
07: 37 :37 Conrad
18:18:26 Scot t
5 020 (16 470)
Scot t I n t i n
Duke-
39: 04: 03
Duke young
21 : 31 :44 Cernan
7 370 (24 180) Cernan S C M tt
%ximum di f fe rence in radii of geocentric spheres in te rcepted by vehic le .
bIncludw uLIs of crew.
CCoaputed from termination of t h r u s t fo r lunar orbit inacr t ion t o beginning of t h rus t for t ransear th in j ec t ion .
%be spmt ou t s ide spacecraf t using an autonowus l i f e w o r t myatem.
b i s t a n c e u s u r a d r ad ia l ly from mpacacraft and dong lclo sur face .
Time beginn and endo a t c roaa ing of veh ic l e o u t l i n e when exit ing and en te r ing t h e mpacecraft.
sj w
APPENDIX E - FLIGHT SPACECRAFT CHECKOUT HISTORY
.
E-1
Spacecraf t lmission
CSM-020 Apollo 6
CSM-002 CSM-009 CSII-011 C SM-012 CSM-017 Test /operat ion A404 AS-201 AS-202 Apollo I Apollo 4
Factory I I 1 I
Indiv idua l and combined Sept. 3, 1965 Sept. 19, 1965 Mar. 1, 1966 June 13, 1966 %ov. 27, 1966 Oct. 10, 1967 systems test completed I I I I I I
In tegra ted systems test completed
Ready to ship:
Sept. 30, 1965 O c t . 19, 1965 Apr. 2, 1966 Ju ly 14, 1966 Dec. 3, 1966 Oct. 27, 1967
Command module Oct. 8, 1965 O c t . 24, 1965 Apr. 15, 1966 Aug. 25, 1966 Dec. 22, 1966 Nov. 22, 1967 Service module Oct. 6, 1965 O c t . 22, 1965 Apr. 9 , 1966 Aug. 9 , 1966 Dec. 19 , 1966 Nov. 9, 1967
bLaunch S i t e
Delivered:
Comnand module Service module
dCommand and service
dCombined systems test
dAl t it ude tests
modules mated
completed
completed
Command and s e r v i c e mod- u l e moved to launch complex
Conrmand and service mod- u l e mved to v e h i c l e assembly bui lding
kt. 10, 1965 kt. 7, 1965
kt. 29, 1965
kt . 29, 1965
O c t . 26, 1965 O c t 27, 1965
Nov. 27, 1965
Dec. 6, 1965
Dec. 20. 1965
Dec. 27, 1965
-
Apr. 18, 1966 Apr. 11. 1966
May 11, 1966
May 14, 1966
June 11, 1966
July 2, 1966
Aug. 26, 1966 Aug. 10, 1966
Aug. 29, 1966
Sept. 14. 1966
Nov. 29, 1966
Jan. 6 , 1967
Dee. 24, 1966 Dec . 21, 1966
Dec. 28, 1966
June 20, 1967
Sov. 23, 1967 (C)
Dec. 5. 1967
Dee. 8 , 1967
4
TABLE E-I.- BLOCK I FLIGHT COMMAND AND SERVICE IDDULE CHECKOUT HISTORY - Concluded
~
T e s t lopera t ion
Command and serv ice mod- u l e in tegra ted sys- tems test completed
Cowand and serv ice mod- u l e e l e c t r i c a l l y matec t o launch vehic le
Overall test completed
Assembled space vehicle moved to launch complex
F l i g h t readiness test completed
Countdown demonstra- t i o n test completed
F ina l phase of count- down and launch
CSM-002 A-004
Nov. 8, 1965
Nov. 19 , 1965
Nov. 22, 1965
-
Jan 13, 1966
-
Jan. 20, 1966
~~~ ~
CSM-009 As-201
Jan. 18, 1966
Jan. 19. 1966
Feb. 2, 1966
-
Feb. 13, 1966
Feb. 10, 1966
Peb. 26, 1966
Spacecraftlmission
CSM-011 AS-202
July 5 , 1966
Ju ly 21, 1966
Ju ly 24, 1966
-
Aug. 9, 1966
Ju ly 29, 1966
Aug. 25, 1966
CSM-012 Apollo I
Jan. 11, 1967
'Jan. 27, 1967
-
CSM-017 Apollo 4
June 28, 1967
July 23, 1967
Aug. 2 , 1967
Aug. 24. 1967
Dct. 24, 1967
Sept. 27, 1967
Nov. 9. 1967
CSM-020 Apollo 6
Dec. 30, 1967
Jan. 12, 1968
Jan. 24. 1968
Feb. 5, 1968
Mar. 1 2 , 1968
Mar. 31, 1968
Apr. 4 , 1968
aSM-017 was destroyed during t e s t i n g on 10125166.
bCSM-002 launched from White Sands Missile Range, New Mexico.
'Data not ava i lab le .
dConducted in Operations and Checkout Building.
eNo t e s t i n g i n the Operations and Checkout Building w a s planned for CSM-017 and CSI4-020; however, because of t h e
The serv ice module w a s replaced v l t h SM-020, and SM-014 was assigned for use v i t h CM-020.
launched from A i r Force Eastern Test Range o r Kennedy Space Center. Al l o ther f l i g h t command and serv ice modules
Apollo I f i r e , an in tegra ted systems test w a s performed on CSM-017 in t h e Operations and Checkout Building. a f t e r which modifications w e r e made. CSII-017 was then moved t o the vehic le assembly bui lding and t h e scheduled checkout was resumed.
f In te r face / in tegra ted test.
gSpacecraft destroyed by fire on January 27, 1967, during "plugs out" por t ion of o v e r a l l test.
!
I i
CSM-101 CSM-103 CSM-104 Tea t / o p e r a t fan
Apollo 7 Apollo 8 Apollo 9 CStl-106 CSM-107 CSM-108
Apollo 10 Apollo 11 Apollo 12
Delivered
Command and s e r v i c e a
modules mated
aCombined systeme test completed
A l t i t u d e tests completed
a
Command and s e r v i c e mod- ' ule moved t o launch
complex 34
Command and service mod- u l e moved t o v e h i c l e assembly bui ld ing
Assembled space vehic le moved t o launch com- plex 39
Individual and combined Mar. 18, 1968 June 2. 1968 Ju ly 20, 1968 Sept. 8, 1968 Oct. 12, 1968 systems test completed
In tegra ted system test Apr. 29, 1968 J u l y 21, 1968 Aug. 31, 1968 Oct. 19, 1968 Dec. 6, 1968 completed
Ready t o s h i p May 29, 1968 Aug. 11, 1968 Oct. 5 , 1968 NOV. 24, 1968 Jan. 22, 1969
J
Jan. 20, 1969
Feb. 3, 1969
Mar. 27, 1969
b y 30, 1968
rune 11. 1968
lune 19, 1968
luly 29, 1968
4ug. 9. 1968
Aug. 12, 1968
Aug. 22, 1968
Aug. 27, 1968
Sept. 22. 1968
-
O c t . 7 , 1968
Oct. 9 , 1968
Dct. 6, 1968
3ct . 8, 1968
Dct. 24, 1968
Nov. 18, 1968
-
Dee. 3, 1968
Jan. 3, 1969
Nov. 25, 1968
k v . 26, 1968
Dec. 16, 1968
Jan. 17, 1969
-
Feb. 6 , 1969
Mar, 11, 1969
Jan. 23, 1969
Jan. 29, 1969
Feb. 1 7 , 1969
Mar. 24, 1969
-
Apr. 14, 1969
?4ay 20, 1969
klar. 28. 1969
Apr. 2, 1969
Apr. 21, 1969
June 9, 1969
June 30, 1969
Sept. 8, 1969
,-
TABLE E-11.- BLOCK I1 FLIGHT COMMAND AND SERVICE MODULE CHECKOUT HISTORY - Continued (Apollo 7 through Apollo 12)
Testfoperat ion
'Command and serv ice mod- ule in tegra ted sys- tems test completed
'Command and serv ice mod- u l e e l e c t r i c a l l y mated t o launch vehic le
'Overall test completed
F l ight readiness test completed
Countdown demonstra- t i o n test completed
F ina l phase of count- down and launch
CSM-101 Apollo 7
4ug. 27, 1968
9ug. 30, 1968
Sept. 4, 1968
Sept. 25, 1968
Sept. 17, 1968
Dct. 11, 1968
, CSM-103 Apollo 8
Nov. 2 , 1968
Nov. 4, 1968
Nov. 6, 1968
Nov. 11, 1968
Dec. 5. 1968
Dec. 21, 1968
Spacecraftlmission
CSM-104 Apollo 9
Dec. 11, 1968
Dec. 26, 1968
Dec. 27, 1968
Jan. 16, 1969
Feb. 12, 1969
Mar. 3, 1969
CSM-106 Apollo 10
Feb. 13, 1969
Feb. 27, 1969
Mar. 3, 1969
Apr. 7, 1969
Apr. 29, 1969
May 18, 1969
CSM-107 Apollo 11
Apr. 22, 1969
May 5, 1969
May 6, 1969
June 1, 1969
June 26, 1969
July 16, 1969
CSM-108 Apollo 1 2
July 7, 1969
July 16, 1969
Ju ly 17, 1969
Sip t . 29, 1969
O c t . 23, 1969
Nov. 14, 1969
aPerfonned in Operations and Checkout Building (renamed Manned Spacecraft Operations Building).
bIntegrated systems t e a t , electrical mate and o v e r a l l test were conducted in t h e vehicle assembly bui lding on the, Apollo 9. 10. 11 and 12 vehicles. These operat ions were conducted a t the launch site on the Apollo 7 , 8, 13, 1 4 , 15, 16 and 17 vehicles .
TABLE E-11.- BLOCK I1 FLIGHT COMMAND AND SERVICE WU)DULE CHECKOUT HISTORY - Continued (Apollo 1 3 through Apollo 17)
Tes t /opera t ion
Spacecraf t / m i s s i on
CSM-109 CSM-110 CSM-112 CSM-113 CSM-114 Apollo 1 3 Apollo 14 Apollo 15 ApoLLo 16 Apollo 1 7
Indiv idua l and combined systems test completed
In tegra ted syatems t e a t completed
Ready t o sh ip
Mar. 16, 1969
Apr. 8, 1969
June 25, 1969
Delivered
Connuand and s e r v i c e a modules mated
aCombined Bysterne test
a
completed
A l t i t u d e tests completed
Conrmand and s e r v i c e mod- ule moved t o v e h i c l e assembly bui ld ing
Assembled space v e h i c l e moved t o launch com- plex 39
bConmand and s e r v i c e mod- u l e in tegra ted t e a t completed
~~~
Apr. 2, 1969 ‘Nov. 5, 1969
May 7. 1969 Nov. 24, 1970
Nov. 17, 1969 Jan. 11, 1971
Jtme 25, 1969
June 30, 1969
J u l y 7, 1969
Sept. 12, 1969
Dec. 9, 1969
Dec. 14, 1969
Jan. 5, 1970
Kennedy Space Center
Nov. 19, 1969
Nov. 24, 1969
Feb. 2, 1970
‘Sept. 1, 1970
Nav. 4, 1970
Nov. 9, 1970
Nov. 18, 1970
Jan. 14. 1971
Jan. 18, 1971
Apr. 9, 1971
May 8, 1971
May 10, 1971
May 18, 1971
’Dec. 3, 1970
Mar. 17, 1971
J u l y 26, 1971
Aug. 1, 1971
Aug. 2, 1971
Sept. 13 , 1971
O c t . 21, 1971
Dec. 7, 1971
Dec. 13, 1971
‘Jan. 3, 1972
May 8, 1971
dAug. 2 , 1971
Mar. 17, 1972
Mar. 24, 1972
Mar. 28, 1972
May 9, 1972
June 19, 1972
Aug. 2 2 , 1972
Aug. 28, 1972
Sept. 11, 1972
. c
TABLE E-11. - BLOCK I1 FLIGHT COMMAND AND SERVICE MODULE CHECKOUT HISTORY - Concluded (Apollo 13 through Apollo 1 7 )
,. .. -
~ ~~
T e s t / opera t i o n
bCommand and serv ice mod- u l e e l e c t r i c a l l y mated t o launch vehic le
bOverall test completed
F l ight readiness test completed
Countdown demonstration test completed
F ina l phase o f count- down and launch
CSM-109 Apollo 13
Jan. 18, 1970
Jan. 19, 1970
Jan. 25, 1970
Mar. 18, 1970
Apr. 11, 1970
CSN-110 Apollo 14
Spacecraftfmission
Dec. 13, 1970
Dec. 14, 1970
Dec. 16, 1970
Jan. 12, 1971
Jan. 31, 1971
CSM-112 Apollo 15
June 7 , 1971
June 7, 1971
June 13, 1971
J u l y 7, 1971
J u l y 26. 1971
CSM-113 Apollo 16
Feb. 21. 1972
Feb. 22, 1972
Feb. 29, 1972
Mar. 27. 1972
Apr. 16, 1972
CSM-114 Apollo 17
Oct. 11, 1972
Oct. 17, 1972
O c t . 19, 1972
Nov. 15, 1972
Dec. 7. 1972
$erformed i n Operations and Checkout Building (renamed Manned Spacecraf t Opera t iom Building).
bIntegrated s y s t e m test, electrical mate and o v e r a l l test e r e conducted i n t h e v e h i c l e assembly bui ld ing on t h e Apollo 9, 10, 11 and 12 vehic les . 1 6 and 17 vehic les .
These operat ione were conducted a t the launch site on the Apollo 7, 8, 13, 1 4 , 15,
cJ-mission modif icat ions and retest w e r e accomplished p r i o r t o in tegra ted s y s t e m test.
dCommand and service modules s tored a t f a c t o r y f o r approximately two months p r i o r t o shipment.
eCryogenic system modif icat ions and r e t e s t performed a f t e r a l t i t u d e test.
fFollowing in tegra ted test, t h e Apollo 16 spacecraf t w a s nuved back t o t h e Manned Spacecraf t Opera t iom Building f o r replacement of a command module reac t ion cont ro l system propel lan t tank and modif icat ion of t h e docking r ing. T h e spacecraf t w a s then r e i n s t a l l e d on the launch vehic le i n t h e vehic le assembly bui ld ing and t h e s t a c k w a s moved t o t h e launch pad on 2/8/72. 'Retest w a s conducted 2/14/72.
M 4
--
LU-5 Tea t l o p e r a t i o n
Apollo 11
E-a
Ln-6 Apollo 12
TABLE E-111.- FLICHT LUNAR M0DUL.E CHECKOUT HISTORY (Apollo 5 through Apollo 12)
I n t e g r a t e d test War. 10, 1967 Jan. 31, 1968
Oct. 12, 1968 Oct. 9 , 1968
June 14, 1967 I Fina l engineering eva lua t ion acceptance t e a t
Jan. 7, 1969 t h r . 23. 1369 Jan. 11, 1969 Mar. 22. 1969
Ready t o s h i p : Ascent s t a g 8 Descent s t a g e
June 21, 1967 June 21. 1967
May 17. 1968
June 12, 1968 June 4 , 1968
Delivered:
Ascent s t a g e Descent s t a g e
'Ascent and descent s t a g e s mated
'Combined systems t e s t completed
'Alti tude t e s t a completed
Lunar w d u l e moved t o launch complex 37
Spacecraft moved t o v e h i c l e assembly bui ld ing
Assembled apace vehic le m e d
I Lunar m d u l e COmbin8d s y e t m
t o launch complex 39
t e a t completed
F l i g h t readiness test c q l s t e d
Countdown demonatrstion test completed
F i n a l phase of countdam and launch
Kennedy Space Center
June 23. 1967 June 23. 1967
Ju ly 13. 1967
July 30, 1967
- Nov. 20. 1967
(C)
Dec. 22. 1967
Jan. 18. 1968
Jan. 22, 1968
Junc 1 4 . 1968 June 9, 1968
June 30, €968
J u l y 1, 1968
Sept. 27, 1968
-
Dee. 3. 1968
Jan . 3, 1969
'Dec. 7, 1968
Jan. 19. 1969
Feb. 12 , 1969
Har. 3. 1969
~
May 25. 1968
Oct. 2, 1968
O f t . 21, 1968
Dec. 13. 1968
Dec. 31. 1968
Feb. 18. 1969
Oct. 16. 1968 Oct. 11. 1968
Nov. 2, 1968
Ibv. 6 , 1968
Dec. 6 , 1968
-
Feb. 6 , 1369
Mar. 11. 1969
'Feb. 10. 1969
H.r. 27, 1969
Apr. 29, 1969
Hay 18, 1969
Jan. 8 , 1969 Jan . 12. 1969
Feb. 14 , 1969
Peb. 17, 1969
Mar. 25, 1969
-
Apr. 14, 1969
May 20, 1969
Apr. 18. 1969 I
June 2. 1969
Jum 26. 1969
Ju ly 16. 1969
Mar. 24, 1969 Mar. 24, 1969
Apr. 28. 1969
May 1, 1969
June 16, 1969
-
June 20. 1969
Sept. 8. 1969
' Ju ly 5 . 1969
S8pt. 18. 1969
Oct. 23. 1969
Nov. 14, 1969
b - 1 v u t h e only unmanned f l i g h t lunar a d u l e .
bOperatiolu were performed in t h e Operatiolls m d Checkout Building (renamed Wanned Spacecraft Operations Building).
'Apollo 5 launch p d t e s t a p r i o r t o f l i g h t r u d i n c e s t e e t conais ted of l u n a r m d u l e i n t e g r a t e d systems t e a t ,
%es ta mra conducted in vehicle assembly bui ld ins .
8imulated miasion. and m r d € teat . 1 and 2.
.
ORIGINAL PAGE IS OF POOR QUALm
E-9
Nov. 8, 1969 Nov. 13. 1969
Kmnedy Space Center
. TABLE E-111.- PLICAT LUNAR WDULE CBECRODT EISTORY - Concluded
(Apollo 1 3 through Apollo 17)
~~ ~~
Test lopera t ion
F a c t o w
Fina l engineering eva lua t ion Nay 18. 1969 acceptance t e s t
Ready t o sh ip :
Ascent s t a g e Descent s t a g e
Delivered :
Aectnt s t a g e Deecent s t a g e
'Ascent and descent s tage6 mated
'Combined s y s t e m test completed
'Alti tude tests completed
Spacecraf t w v e d t o v e h i c l e assembly b u i l d i n g
Assembled space vehic le w v e d t o launch complex 39
Lunar module combined 9 s t c m s test completed
F l i g h t readiness test completed
Countdown demonstration test completed
F ina l phase of countdown and launch
June 24, 1969 June 25, 1969
June 27, 1969 June 28, 1969
J u l y 15 , 1969
J u l y 22, 1969
Scpt. 20, 1969
Dac. 10 , 1969
Dec. 15, 1969
Jan . 5 . 1970
Peb. 24. 1970
Nar. 18. 1970
Apr. 11. 1970
(e 1
Aug. 25, 1969
Nov. 24, 1969 Nov. 24, 1969
Jan. 20, 1970
Jan. 22, 1970
June 22. 1970
Nov. 4, 1970
mv. 9. 1970
Nov. 16. 1970
Dec. 14. 1970
Jan. 12. 1971
Jan. 31. 1971
P
(e )
Sapt. 21. 1970
(el
Peb. 24. 1971
Nov. 6, 1970 Nov. 16 , 1970
Feb. 9. 1971
Feb. 12. 1971
Apr. 6, 1971
b y 8, 1971
Nay 11, 1971
Nay 17. 1971
June 10. 1971
July 8 . 1971
July 26. 1971
Nay 14, 1971 nily 6. 1971
( f )
( f )
Oct. 19 , 1971
Dec. 8 . 1971
Dec. 13, 1971
'Jan. 4 , 1972
Feb. 24, 1972
Nar. 27. 1972
Apr. 16, 1972
(6 )
Nay 23. 1971
June 14. 1971 June 14. 1971
Nar. 1 2 , 1972 Mar. 1 2 , 1972
Nay 18. 1972
June 7, 1972
J u l y 25. 1972
Aug. 24, 1972
Aug. 28. 1972
Sept. 6 , 1972
O f t . 4, 1972
Nov. 15 , 1972
Dec. 7. 1972
%-1 was the only unmanned f l i g h t l u n a r m d u l e . bOperations e r e p e r f o w d i n the Operatlona and Checkout Building (renamed Manned Spacecraft Operations Building).
CApollo 5 launch pad tests p r i o r t o f l i g h t readiness test cons is ted of lunar module i n t e g r a t e d systems t e s t ,
dTes ts were conducted in vehic le assembly bui ld ing .
e I a t e g r a t e d t e a t combined wi th f i n a l engineering eva lua t ion acceptance test. fData not a v a i l a b l e . %he Apollo 16 s p a c e c r a f t WM m v e d back t o the Manned Spacecraft Operations Building a f t e r combined mystcms t e a t
The spacecraf t was r e i n s t a l l e d on the launch vehic le in the v e h i c l e assembly bui ld-
simulated mlssion. and o v e r a l l t e a t s 1 and 2.
f o r camand module modi f ica t ions . i n g m d t h e s t a c k wan mved back t o the launch pad on 2/6/72.
?
F- 1
. APPENDIX F - FLIGHT ANOMALIES
This appendix contains abbreviated descr ip t ions of s i g n i f i c a n t spacecraf t systems malfunc- t i o n s as w e l l as o ther f l i g h t hardware problems t h a t were termed "anomalies" and are discussed in t h e anomaly sec t ions of the Apollo 4 through Apollo 17 Mission Reports. of problems which occurred o r were noted during f l i g h t and, in some cases, a f t e r f l i g h t . I n ad- d i t i o n t o t h e statement of the problem, t h e causes and cor rec t ive ac t ions are b r i e f l y descr ibed. In general , t h e anomalies per ta in t o the spacecraf t (CSM, LM, and SLA), government-furnished equipment used by the crews (GFE), lunar surface experiments (ALSEP), lunar o r b i t a l experiments (SIM), and the lunar roving vehic les (LRV). I n cases where t h e same problem o r a c l o s e l y re- l a t e d problem occurred on rmre than one mission, the appropriate missions are i d e n t i f i e d . reference given f o r each anomaly is the appl icable Mission Report. When more than one reference i s given, the addi t iona l references are appl icable Anomaly Reports t h a t were published f o r anom- a l i e s t h a t were not completely resolved a t the time of Mission Report publ icat ion.
The lists c o n s i s t
The
F- 2
Anomalv lo. Statement
!Instrumentation 5-Vdc re ference vol tage de- I creased a f t e r CU/W .cp a r a t i o n . I Holes in M a f t hea t s h i e l d a b l a t o r .
Real-tfme c o m n d (ItTC) 1 3 vas not tranamitted.
Pyrotechnic b a t t e r y v o l t a g e s d i d not r e t u r n t o open-c i rcu i t l e v e l .
CM VHF recovery antenna f a i l e d t o lock into poo i t i o n .
Guam l o s t S-band d a m - link s i g n a l a t WlSn separa t ion .
CSK S-band rece iver l o a lock.
SPS ahutdovn van l a t e during second f i r i n g .
S t a t e v e c t o r update corn uands not accepted by s p a c e c r a f t .
10 Spacecraft i n t e r n a l hen load was l o v e r than pre d ic ted . r e s u l t i n k in lover-than-expected eva o r a t o r i n l e t and o u t l e t temperatures and steam back pressure .
11 I n t e r f e r e n c e b e t v n n apex cover and RCS en- gines.
12 D m q e to , recovered mi parachute.
13 Foreign mterirl in cabin pressure r e l i e f V a l = .
Vehicle/ Equipment
CSK-011 CSK-017
CSM-017
KSFK
CW-017
CSM-017
HSFK
CSM-017
CSM-017
SFn
CSM-017
CSM-017
CSM-017
EN-017
Cau
eC/SM separa t ion monitor burr off dur ing e n t r y and viring exposed t o e n t r y p l a s m . An ing did not blow fuse becausa of wrong fuae size and e r r o r ! in wiring.
!lanufacruring and q u a l i t y Ue. f i c i e n c p a t vendor.
3pe ta t ions procedural error . :omand executed before v e r i . fS.cation received from pre- rious command.
Leakage cur ren t of pyrotech- Tic i n i t i a t o r s a f te r f i r i n g .
Yarginal deploynent apring.
Signal percurba t ions by RCS t h r u s t e r plumes and improper reacquis i t ion procedure.
g u l l s in spacecraf t antenna pat t e r n .
Data- de lays due t o instrumen- t a t i o n , transmission and proc easing =re g r e a r e r than cx- ?ec ted . Poor a l i g n m n t of updata buf- rer a t ground s t a t i o n caused i i s t o r t i o n of t ransmi t ted si f n a l . Heat loads vere v i t h i n pre- i ict i ve c a p a b i l i t y .
A t apex cover J e t t i s o n , love1 l i p of apex cover caught on lover left c o m e r of engine mounting panel.
RCS oxidizer dump dur ing lMC i n g sequence.
H - f i l m inges ted during e n t y ,
s h i e l d s completed.
None.
None requi red .
None.
viered t o insure cor- r e c t d a t a in the anten pos i t ion programer .
None.
incorporated i n t o per- fornance and i n t e r f a c e specs.
sure c o n t r o l valve s t i n g f o r Apollo 6 ba on updated p r e d i c t l o Block XI design and u d c o n t r o l c a p a b i l i e l imina tes problem o w e d vehic les .
Apollo 6; block I1 figuration bas adeq clearance.
Oxldizer q u a n t i t y de- c reased andlor landing with p r o p e l l a o t s on board.
None requi red . Apollo I
ORIGINAL PAGE IS OF POOR QUALEY
References
KSC-PA-R-68- KSC-IT-R-67-4 (Rev. A)
MSC-PA-R-68-1 SC-PT-R-67-3
KSC-PA-R-68-1 KSC-PT-R-67-11
MSC-PA-68-1 MSC-PT-R-67-1
KSC-PA-R-68-1 MSC-PT-R-67-6
HSC-PA-R-68-1 MSC-PT-R-68-1
KSC-PA-R-6 8- 1 KSC-PT-R-68-4
MSC-PA-R-68-1 HSC-PT-R-68-3
YBC-PA-R-68-1 MSC-Fl’-R-68-1(
MSC-PA-R-~E-~ SC-PT-R-68-5
MSC-PA-R-68-1 MSC-FT-R-67-11
H S C - P A - R - ~ ~ - ~ MSC-PT-R-68-9
(Rev. A)
MSC-FT-R-68-1:
!
i i
F- 3
. Anomaly XO. I S t a t enent
Premature shutdovn of f i r s t descent engine f i r i n g .
Abrupt change i n cabin pressure leak r a t e .
O u t 4 f -phase i n q c a t ion from descent engine pro p e l l a n t shutof f valves.
Abrupt changes i n space c raf t - rece ived UHF s i g n a l s t rength .
Excessive c o n t r o l engin propel lan t usage (i tems 6, 7. 8 and 9 a r e re- l a t e d ) .
Discrepant propel lan t manifold pressure in- di c a t ions .
System A o x i d i z e r shut- o f f valve unlatched fro; open p o s i t i o n v i t h o u t c o m d .
Thrust c h h e r of up- f i r i n g engine in c l u s t e 4 f a i l e d .
High engine c l u s t e r temperatures.
10 Descent stage f lber - g l a s s thermal s h i e l d f a i l e d .
ll No i n d i c a t i o n of adapt- er panel deployment.
12 Separa t ion d i s t a n c e m n i t o r s d i d not h c - t i o n dur ing abor t s tag- ing.
Vehicle/ Equipment
LM-1 ~~ ~~
LM-1
LM-1
LM-1
LM-1
LH-1
W-1
LM-1
LH-1
IA-1
SLA
IH-1
Caus e
Slover-than-normal t h r u s t bu i ldup ceused by start a t less than fu l l tank p r e s s u r e .
unknam.
Poss ib le open or shor ted c i r - c u i t causing shutoff b a l l va lve t o c l o s e , or p o s s i b l e reed switch z a l h c t i o n .
I n t e r m i t t e n t opera t ion of RF stage o f t h e d i g l t a l c o m m d assembly or t h e coaxial cable connecting t h e d i p l e x e r t o t h e d i g i t a l c o m d assembly.
Incor rec t configuration of PCNCS d i g i t a l a u t o p i l o t after s tag ing . Calcu la t ions f o r t h r u s t e r "on" t i m e used com- bined descent /ascent s t a g e i r e r t i a cons tan ts after descent s t y s e p a m t i o n .
Fuel deple t ion vas obscurred by t h e e f f e c t s of b ladder leakage and t h e m i f o l d p e s sure sensor sensing helium pressure .
Pover was inadver ten t ly ap- p l i e d t o t h e valve c l o s e co i l f o r 51 minutes. r a i s i n g i t s tempersture t o 325' F. Sub- sequent va lve opening, vapor- i z a t i o n of oxid izer trapped above upper magnet i n va lvc , and cross feed opening pres- sure drop unla tched t h e valve
Excess iw t h r u s t e r act i v l t y r e s u l t e d i n opera t ion v i t h lov o x i d i z e r manifold pres- s u r e and v i t h he l ium/ lue l mlr t u r e i n f u e l manifold. (This condi t ion ceuies accumulation of explosive res idue i n com- bus t ion chamber.)
Excessive c o n t r o l e n g n e ac- t i v i t y ( s e e i t e m 5 ) .
High temperature i n d i c a t i o n s irom sensors beneath t h e r m l s h i e l d at abor t s t a g i n g v e r e probably caused by t h e w 1 s h i e l d f a i l u r e ,
Panels deployed b u t no i n d i - c a t i o n vas rece ived from l i m - it sv i tches . Cause unknown.
Unknovn .
Correc t ive Action
None.
None.
Valve paclragcs replace1 on Apollo 9 and 10 luni modules. improved man- ufac tur ing techniques , md added emphassis on q u a l i t y c o n t r o l .
Nev acceptance v i b r a t i c t e s t levels (planned p r i o r t o m-1 mission).
lone requi red .
None I
Yone.
gone.
Yone.
None r e q u i r e d (system not used on manned mefits 1.
None requi red ( n o t usec 30 manned f l i g h t s ) .
- !is s ioi
Apollo
A p c l l o
Apollo
Apollo
4pOllO
kpollo
4 p O l l O
4pOllo
RpOll0
k p o l l 0
kpollo
Raferenccs
MSC-PA-R-68-'
KSC-PA-R-68-' HSC-PP-R-69d
MSC-PA-R-68-7 HSC-PT-R-68-1 (Report no. :
H S C - P A - R - ~ ~ - ~ HSC-FT-R-68-1 (Report no. 4
MSC-PA-R-68-1 MSC-IT-R-68-1 (Report no. 1
MSC-PA-R-68-1 MSC-IT-R-68-1 (Report no.
M S C - P A - R - ~ ~ - ~ MSC-FT-R-68-1 (Report no. I
Five press- and tem- p e r a t u r e sensors f a i l e d dur ing abort s tag ing .
Cause Statement
None.
Correcti-re Action Yiss ions i e f z r e n c e s
Apollo 5
Rendezvous radar antenn Poss ib le f a i l u r e of t r a n s - v i b r a t i o n measurement ducer s i g n a l wires. was i n t e r m i t t e n t .
MSC-PA-R-68-7
None.
ria.
1
2
3
4
5
6
A.-.c7A.v S t a t enent
An a-c e s s e n t i a l e lec- t r i c a l 104. t r a n s f e r oc cur red .
E r r a t i c data.
Computer update r e j e c - t i o n s .
Excessive cabin-to-ambi e n t d i f f e r e n t i a l pres- sure.
Oxygen surge tank prea- s u r e varied abnormally.
Abnonml itructural per formsnce dur ing launch
MSC-m-R-68-2
phase.
i p o l l o 6 MSC-PA-R-68-9 MSC-PT-R-68-38
Vehicle/ Equipnent
CSM-OM
CSM-020
CSH-OPO
CSM-020
C 5 M - 0 2 0
SLA
CSM-020
CSM-OM
rSH-020
ipollo 6
ipol lo 6
kpollo 6
go110 6
~
Cause
Short i n cryogenic tank 1 f w c i r c u i t .
MSC-PA-R-68-9 MSC-PT-R-68-k
MSC-PA-R-68-9 MSC-PP-R-68-3:
MSC-PA-R-68-9 MSC-PT-R-68-2;
MSC-PA-R-68-9 MSC-PT-R-68-2t
Corona discharge of 3000-volt Ic p o t e n t i a l of VAC-IOR pump:
7
8
Noise pulses impressed on s e ~ vice module umbi l ica l . prob- ably because of inadequate sh ie ld ing .
VHP recovery bewon o r survival beacon s i g n a l Mt rece ived by ARIA.
Dosimeter measurerents e m t i c .
No vent hole t h r o w boost p r o t e c t i v e cover at steam duct o u t l e t .
One o r bo th oxygen check valves d i d not seat properly.
Facesheet bond too w e a b f o r I n t e r n a l panel pressures achieved.
? o a t n i g h t aalysis showed :hat survival beacon s i g n a l can not received. Cause un- m o m .
E l e c t r i c a l n o i s e on dosimctei iutput l i n e s .
J i r i n g t o yau engines wan rc- e r s e d at t e d n a l boards dur ng engine i n a t a l l a t i o n .
~~
Correc t ive Action
lone requi red . Fans *edesigned f o r Block I reh ic les .
VAC-ION pumps d isab le , on Apollo 7, 8 and 9. Pumps redesigned f o r Apollo 10 and subse- quent.
Multi-point grounding used on a h i e l d s f o r Block I1 s p a c e c r a f t . Uplink blocked on Apo 7 when not updating. Relay t o preclude noi! t ransmiss ion added t o s p a c e c r a t t f o r Apollo 9 and subsequent.
Mandatory inspec t ion p o i n t s e s t a b l i s h e d t o assure proper manulac t u r i n g and alignment.
Spring added t o assuri proper s e a t i n g at lov d i f f e r e n t i a l p ressure
Cork covering added tl: reduce temperature ant i n t e r n a l pressure . PI e l s vented t o ambient Inspec t ion and qua l i t ! c o n t r o l procedures changed t o v e r i f y soul cons t ruc t ion .
None requi red .
Hone requi red .
Funct iona l t e s t s per- lonned on spscecraft l o r Apollo 7. 8 and 9. I d e n t i f i c a t i o n sleevin, sdded on subsequent spacecraft i n a d d i t i o n to f u n c t i o n a l tests.
~
: i s s f o n s I Aaferences
go110 6 WC-PA-R-68-9 I MSC-PT-R-68-3;
MSC-PT-R-66-29
,
ORIGTNAL PAGE IS OF POOR QUALm
F- 5
' t i s s i o n s
Apollo 7
Apollo 7
Apollo 7
Apollo 7
Apollo 7
Apollo 7 pol lo 8 p o l l o 9 poll0 10 pollo ll
Apollo 7
Apollo 7 Apollo 8 p o l l 0 1 2
.
References
MSC-PA-R-68-1
MSC-PA-R-68-i
MSC-PA-A-68-1
MSC-PA-R-68-1
MSC-PA-R-68-1
MSC-PA-R-68-1 MSC-02417
MSC-PA-R-68-1
MSC-PA-R-68-1 MSC-PI'-R-69-1
kio-aly No. I Statement
O-ring swel l ing caused by aodium hypochlor i te i n drink- i n g water .
Solder bal l found i n r e l a y may have caused t h e condi t ion
Anomaly could not be repro- produced p o s t n i g h t ; symp- toms i n d i c a t e d breakout switch temporar i ly i d l e d t o open when c o n t r o l l e r was re- turned wi th in t h e d e t e n t .
Quality c o n t r o l problems.
Panel fully deployed i n l t i - e l ly . b u t rebounded because re ten t ion cable was caught i n ihannel. Retention cable YILS
l a t e r re leased and panel was re ta ined f u l l y deployed.
h t g a s s i n g of s i l i c o n e o i l 6 f r o m RTV s e a l i n g m a t e r i a l .
ce module quad C in-
b i l i c a l found post-
O-ring m a t e r i a l change6 t o e thylene propylene.
All r e l a y s involved i n c r i t i c a l swi tch ing func t i o n s were made redund- a n t .
None requi red . Improve design used f o r Apollo 8 and subsequent.
Manufacturing and t e s t procedures improved.
None requi red . Panels J e t t i s o n e d on Apollo 6 and subsequent.
P a r t s us ing RTV m a t e r i a precurcd i n vacuum at e l e v a t e d temperatures, e f f e c t i v e on Apollo 9.
- ::a.
1 -
2
3
4
5
6
1
8
-
Anomly S t e t e s e n t
~~~
:M and voice sub- v r i e r s l a s t on second y S-band transponder.
tomedical instruments- ion leads broken.
r igger on water gun :uck.
t t i t u d e displayed on )A1 s h i f t e d i n p i t c h c is when source switch1 ?om C and B t o S and C
i t a t i o n hand cont ro l le i i i l e d momentarily.
] t r y monitor system Llh\nct ions.
Lapter panel not f u l l y !played.
.ndows fogged.
Vehicle/ Equiprcent
CSM-020
CSM-020
CSM-020
CSM-020
Vehicle/ Equipsent
CSM-101
CSM-101
CSM-101
CSM-101
CSM-101
CSM-101
SLA
CSM-101
mLL0 6
Cause
Probable f a u l t y connection t c t ransducer .
Damage t o SLA dur ing boost ( s e e i tem 6) .
W e r c h a r a n g of b a t t e r i e s p r i o r t o f l i p j l t .
Wires damaged dur ing i n s t a l l a t i o n of umbi l ica l - none asso c i a t e d with n i g h t anomaly.
Correc t ive Action Missions Re f e - e x e s
None requi red .
None requi red .
Apollo 61MSC-PA-R-68-9 I MSC-PP-R-68-37
Apollo 6 MSC-PA-R-68-9 M S C - P P - R - ~ ~ ~ ~
Charging procedures r e Apollo 6 MSC-PA-R-68-9 MSC-m-R-68-30
Apollo 9 and subsequen
v ised . Separa tor ma- terial changed f o r b a t t e r i e s t o b e used on
None r e q u i r e d . Block I1 conf igura t ion pre- c ludes problem.
Cause
NO abnormal i t ies found post- f l i g h t ; problem may have been caused by improper s n i t c h i n g of transponder s e l e c t switch.
Harness and p o t t i n g not suf- t i c i e n t l y flexible.
Correc t ive Action
None requi red .
Wiring i n s u l a t i o n changed from Teflon t o polyvinyl c h l o r i d e and s o f t e r p o t t i n g mater ia l used.
Apollo 6 MSC-PT-R-68-28 A
I
F- 6
- >to . 9
10
11
12
13
14
15
16
17
18
19
20
21
h o z a l y S t L t e r e n t
l i g h t q u a l i f i c a t i o n onmutator f a i l e d .
ater l e a k near v a s t e ater disconnect.
omentary loss of a x usses.
nexpected l o v char&e a t e on b a t t e r i e s A and
ndervol t age ind ica t ion n d-c busses A and B.
'ondenser e x i t tempera- ure of fuel c e l l i n - reased.
r o p e l l a n t i s o l a t i o n alves open v i t h v o l t - ge removed.
o i c e c o m u n i c a t i o n s arbled dur ing launch hme.
r i m evapora tor op- r a t e d e r r a t i c a l l y i n h e automatic mode.
ondensation i n cabin.
cad bag0 spli t mnd wb crumbled.
m t r y b a t t e r y manifold eak . 0th primary Wrn ailed i n lover -equip- Ent bay- floodlights.
Vehicle/ Equipsent
CSM-101
CSM-101
CSM-101
CSM-101
CSM-101
CSM-101
CSH-101
MSFn
CSM-101
CSH-101
CFE
CSM-101
CSH-101
mom 7-
Cause Correc t ive Action :.!issicns Rel'eresces
unar module and f a l l u o d d not prevent s a t i n
fying mission obJective
Poor metd-on-metal s e a l at -ring s e a l used, effec 0-nut connection. i t i v e v i t h Apollo 8.
h o b a b l e i n t e r n a l f a i l u r e of None requi red . Only t iming sequence l o g i c c i r c u i t t h e r use on Apollo 9
Apollo 1
Apollo 7
MSC-PA-R-~S-~: MSC-FT-R-69-7
3vervoltage caused by corona a rc ing of a-c pover within notor-operated cryogenic fan
Line r e s i s t a n c e not conaid-
sv i tch . -
cred i n pred ic t ione .
Condition r e s u l t e d from mid- B a t t e r i e s varmed by range s t a t e o f b a t t e r y charge p l a c i n g them on m a i n nnd l o v temperature. busses 12 minutes p r i o r
t o CM/SM separa t ion . Fuel c e l l 2 removed rro busses and SPS gimbal motors tu rned on t o les t r a n s i e n t loads a: sepa r a t i o n .
Second- bypass va lves op- Radiator h a l f o f Apollo c r a t e d e r r a t i c a l l y because of 8 cool ing system f luahe contaminants. S tudies made t o deter-
mine if modif ica t ion necessary.
Apollo 7
?n
Apollo 7 .Apollo 8 Apollo 9
ipollo 10 1pollo 11
NSC-PA-R-68-15
MSC-PA-R-68-15
Valves vere i n c losed posi- Proper procedure in- t l o n vhen system vas ac t ivn- cluded i n c rev checkl i s Led. Bellows was damaged AOIi nnd b r i e f i n g s . f r o m hydraul ic hammering.
Improper procedures used at Procedures changed ao Apollo ground s t a t i o n s . t h a t pa tch ing of voice
t o MCC accomplished only at Coddard.
Lov, v a r i a b l e hea t loads. Sensor response t o wick Apollo increased by r e l o c a t i o n of aensors and rewval of sponge m a t e r i a l i n sensor ezeas for Apollo 10 and subsequent spnce- c r a f t .
MSC-PA-R-68-15
MSC-PA-R-68-15
Condition expected because Lines i n s u l a t e d on Apollo 7 MSC-PA-R-68-15 >f uninsula ted coolan t l i n e s . Apollo 10 and subsequen
spacecraft. i 3 a g q u a l i t y problem m d menu Menu changed and baga :hoke. inspec ted ror d e f e c t s .
Apollo 7 MSC-PA-R-68-15
able under-torqued B-nuts aa experienced on 2TV-1.
: s u e d cathodes t o degrnde
MSC-PA-R-68-15
MSC-PA-R-68-15
.
. . .
A P O ~ ~ O 7
F- 7
MSC-FT-R-69-5
MSC-PA-R-~B-~
C
Corrective Action
.
Xissions References
- l o .
22 -
23
2h
25
26
Apollo 7 Apollo 8 Apollo 9
Apollo 10 Apollo 11
Apollo 7 ApoUo 8 Apollo 1;' Apollo 8
Anomaly Statement
MSC-PA-R-69-1 MSC-02417
MSC-PA-R-69-1
MSC-PA-R-69-1
Pace g l a s s on mission ;imcrs crtyked.
Vehicle/ Equ ipen t
CSM-101
dater i n docking tunnel CSM-101 rfter landing. I IHF recovery beacon s i g ~ a l not received during iescent.
kpparent f r ee water in su i t supply hoses.
- SO.
1 -
2
3
4
5
6 -
CSM-101
CSM-101
rerence problems experi enced during ground t e s ma n i g h t : 8 . Mission timcr start Lnadvertent l y . 3. Computer progrm elarm.
2 . Central timing equi
A..omaly Statement
? t ry monitor system rrors. .
indovs fogged.
& i n fans noisy.
x s i b l e entry of sea i t e r i n to cabin througl %bin pressure r e l i e f rlve.
:eel cables i n recover: mp broke.
rimwr interphone in- x r a t i v e .
Vehicle/ Equiperent
CSM-103
C91-103
CSM-103
CSM-103
CSM-103
CSM-103
Cause
Cracks probably resul ted fron propa&ion of h a i r l i n e crack introduced during bonding of glass to frame.
[nterim b a l l check vnlve in- s t a l l ed i n top hatch leak?.
Cause unknown. Antenna may not have deployed properly u n t i l s t ab le I a t t i t ude on water was whieved.
Water sepsrator operated in- e f f i c i en t ly because of reser- viclng procedure used a f t e r a l t i t ude run.
a. Associated with oxygen fan cycle.
b. Associated with turning i n t e r i o r l i g h t s on br ight .
C . unknown.
_ _ _ _ _ _ _ ~
AKILU) 8
Cause
Bubble and leak i n acceler- ometer.
Outgassing of s i l i cone o i l s from RTV material.
Possible resonant condition i n ducting.
Water may bave been condensa- t ion. Postflight t e s t s d id not reveal my pressure re- l i e f valve abnormalities.
Recovery loop had exhibited failures previously and was a w n t e d with M auxiliary nylon loop inmtalled by swim- wr.
Probable incorrect operation of interphone.
Corrective Action
mufactur ing procedure evised.
one. Used fo r Awl lo only.
one.
eservlcing procedure hanged. Water removal apab i l i t y rechecked r i o r t o f l i g h t .
one. Aardvare changer o t w r a n t e d .
Ussions 1 References
Units subJected t o t i l t - t a b l e t e s t s .
Cure material p r io r t o in s t a l l a t ion .
lone. Comfortable en- vironmcnt can be main- ta ined without fans.
None required.
FlBCed by permanent ny lon loop fur Apollo U and subsequent space- c r a f t .
!
F- a
Csrrhc t ive dction
Tank f l l l e d t o 80 per- cen t of capac i ty f o r Apollo 9. Urine dump/ oxygen vent i n t e r f a c e changed f o r Apollo 10.
Cause .:issions ?e:=r-z:?x
Apollo 8 EC-PA-R-69-1 Apollo 12 PDOUO 13:
~~ ~~ ~ ~
was found of a d s - ture in i n d i c a t o r housing and oxygen s i d e of tank p r e s s u r i - za t ion system caused by back- up of ur ine dump i n potab le water tank oxygen vent l i n e . Moisture mny have caused er- r a t i c readings.
I I I I
::of
1 -
2
3
4
5
6
1
8
-
C;ati-=E-st
-0pe l lan t i s o l a t i o n five c losures .
:arming te lescope shar :uck i n t e r m i t t e n t l y ant ?chanical counter shal ?came inopera t ive .
ystem f a r automatic m t r o l of cryogenic hy rogen tank pressure %iled.
rroneous docking probe i d i c a t l o o s .
plink conmvrnds not ac- cpted.
a t ry monitor system niled t o s c r i b e dur ing l t ry .
nd ica t ionr of s e r v i c e m p u l a i o n system pro- c u t unbalance.
nexplained master l-.
- CS1E B Correct:*re k z i x
'yrotechnic shock. Valves t o b e checked a f t e r separa t ion of CSM from S-IVB. Valves hav ing no cabin i n d i c a t o r s t o b e cycled a f t e r sep- a r a t i o n .
Proper i n s p e c t i o n of 'in i n " ten ths" counter drum bopped out and jams gem counters t o i n s u r e cor - )n shaft r e s o l v e r . r e c t to le rances .
'robably an i n t e r m i t t e n t open None. : i r c u i t in t h e motor-control : i r c u i t .
k t e n d j r e l e a s e - r e t r a c t switch AOH changed t o r e p u i r e ms not ac tua ted f o r a suffl- holding s v i t c h i n extens : ien t t im t o allow docking e l e a s e position u n t i l r o b e t o f u l l y extend. h y s i c a l separa t ion .
Jnknovn . ecycle up-telemetry v i t c h t o r e s t o r e opera
l i o n .
e following were per- i c r o l l . S t y l u s holder and ormcd f o r Apollo 10 an' mshing contaminated with ubsequent spacecraf t . E Glyptol used ins tem
ic r ibe coa t hardened on
Bck-t l t e . f Lock-ti te. . S t y l u s spr ing load
. Dimension of s t y l u s o l d e r and bushlng v e r i
. Acceptance t e s t s t o
E l e c t r i c a l zero b i a s i n ox- r alarms and wnrn- idher measuring c i r c u i t af- for t h i s system no ter s t o r a g e tank deple t ion . r e d and have been
ed f o r Apollo 10 ubsequent spacecrs durn l change made
imize e l e c t r i c a l zer
t o caut ion and YIvn-
Ap0ll0 5 poll0 11
pol l0 11 poll0 1:
Rpollo 5
pol10 1i
apoiio s
A p o l l O s
RpollO s poll0 It
Rpollo 7 hpollo E
pll0 10 ? o n 0 11
Pip0110 5
Apollo I
p o l l 0 9 p o l l 0 1(
BC-PA-R-69-2
YSC -PA-R-69-2
EC-PA-R-69-2
ISC-PA-A-69-2
4%-PA-R-69-2 ISC-02417
MC -PA-A-b9 -2
MSC-PA-R-69-2
F- 9
~
A-.ooalv
iic . S t a t r c e n t
9
10
11
12
13
1L
15
16
17
1 9
Fuel c e l l 2 condenser e x i t temperature out- s i d e normal range.
Docking s p o t l i g h t f a i l e
I n t e r i o r f loodl ight anomalies.
Computer d i d not respon t o manual e n t r i e s .
Slow r e p r e s s u r i z a t i o n o surge tank.
Docking r i n g separa t ion charge holder came out o r channel and extended beyond periphery of tun ne l s t r u c t u r e .
Descent propulsion sys- tem regula tor manifold pressure dropped.
S u p e r c r i t i c a l helium tank pressure decayed.
Tracking l i g h t f a i l e d .
Push-to-talk switches inopera t ive .
Act iva t ion o f abor t guidance system caused warning i n d i c a t i o n .
Binding of forvard ha tch .
I
SM-104
:SM-104
23M-104
:SM-104
3M-104
XM-104
LM-3
LM-3
LM-3
u4-3
LM-3
LM-3
Cause Correc t ive k c t i o n :cis sio:
Possible coolant loop contam- Procedures developed t o pollo * lna t ion bui ldup i n secondary damp o s c i l l a t i o n s i f p o l l o I
they occur. Secondary p o l l o ! bypass va lve des ign p o l l o changed for Apollo 14 pollo :
iypass valve.
and subsequent space- c r a f t . I r pol lo I
X r c u l t breaker not closed. Crew c h e c k l i s t changed p o l l o ! t o i n c l u e c l o s i n g o f c i r c u i t b reaker p r i o r t s p o t l i g h t deployment.
Zathode eros ion caused fail- Procedures Incorporated p o l l o 7 we of one lamp - broken wire t o insure opera t ion of pol lo I :awed second lamp t o fail. lamps i n f u l l - b r i g h t c o -
f i g u r a t i o n i n ground t e s t s and in f l i g h t .
Possible procedural e r r o r e . none.
Valve I n wrong p o s i t i o n be- Proper alignment to be zause of misaligned -kings. v e r i f i e d on subsequent
spacecra i t .
Holder vas n o t properly re- Retention s p r i n g in- tained. s t a l l e d .
Apollo Apollo 1
4 i r drawn through manifold Ground support equip- Apollo
Probable d e f e c t i v e braze i n Valve conf igura t ion Apollo
and subsequent spscecra I . i n t o tank hea t exchanger dur- ment and procedures mod lng s e r v i c i n g r e s u l t i n g in i f i e d f o r Apollo 10 and p a r t i a l l y blocked hea t ex- subsequent spacecraf t . ?hanger.
squib i s o l a t i o n valve. changed f o r Apollo 1 0
Probable high-voltage break- d o n in pulse-forming network Apollo 10 l i g h t .
Additional t e s t i n g f o r Mod-
i f i e d l i p h t Jsed f o r Apollo 11 and 12.
Probable broken comon wire Operating procedures t o t o switches. inc lude t r o u b l eshoot in8
procedures t o c i r c u w e n problem.
Probable open or s h o r t i n T r i p l e v e l s a r e measure 2 6 - p ~ wire between abor t e l e c t r o n i c s assembly and s i g - launch s i t e . Output pa n a l condi t ioner e l e c t r o n i c s m e t e r s f o r abor t e l e c - assembly. t r o n i c s assembly and
f o r each v e h i c l e at
t r a n s f e r func t ions f o r signal condi t ioner e l e c t r o n i c s assembly meaa- ured on bench.
[n te r fe rence by i n s u l a t i o n Top ha tch s h i e l d ex- )l?mkets and p o s s i b l e insuf- tended t o hatch s t r u c - X c i e n t hatch clearance. t u r e and c learance i n -
creased f o r Apollo 10 and subsequent spacecre
Apollo Apollo
Apollo
Apollo
- , I 1
Apollo
Pe f e r e n c c t
MSC-PA-R-69-2
MSC-PA-R-69-2
MSC-PA-R-69-2
YSC-PA-R-69-2
rISC-PA-H-69-2
SC-PA-R-69-2
MSC-PA-R-69-2
MSC-PA-R-69-2
MSC-PA-R-69-2
MSC-PA-R-69-2
MSC-PA-R-69-2
4SC-PA-R-69-2
F- 10
C&S+ Ccrrecti-re Action k lomiy
!.o . S t a t e n m t !4iss:or;
21
22
23
24
25
26
27
28
29
30
31
32
Fxcesaive clearance betvcen snubber Md Velcro.
Operation of cabin fans, vater lglycol p q s and s u i t compressors during helmcts- off perioda.
Lateral loads probably caused helium diffuser flange t3 contact top deck flange.
Possible bent svi tch l ea f o r contamination preventing mi- croswitch contact.
Suspected helium ingestion in to engine by uncovering of zcro-g C M , due t o high ullage.
Possible regulator contamina- t i o n by backflow during sol- cnoid valve replacement.
Interference vw produced by pieces of H-fllm horn the base heat shield.
Air ingested through sublirn- t o r i n t o coolant loop vhen PLSS was being connected to l iqu id cooled garmcnt.
Snubber redesigned f o r Apollo Apollo 11 and subsequent spacecraft.
Ear pieces provided and Apollo procedures changcd. Ef- Apollo f ec t ive with Apollo I&, muffler added i n l i n e at ou t l e t of water/glycol pump assembly.
Loads predicted t o be Apollo l e s s on Apollo 10- Top deck flange modified on Apollo 11 and subsequent spacecraft.
Microsvitches modifled. A p O l l O
No detrimental e f f ec t . Apollo
Procedures developed for Apollo prevention of contamina- t i o n vhen replacement ol components is necessary.
Spray coating of KEL-F Apollo p l a s t i c subst i tuted f o r H-film on base heat sh i e ld for Apollo 11 anc subsequent spacecraft.
Make-up l i n e on PLSS re- Apollo located t o upstream side of vater shutoff and re- lief d v e f o r Apollo 11 and subsequent miasions.
Forvard hatch door stop (snubber) would not hol' hatch open.
Cabin noise le=l hi@.
S t ruc tu ra l contact at S-IC shutdown.
Data entry and display assembly operator e r ro r Hat. Descent engine f l r i n g rough at 27-percent t h r o t t l e .
Regulated helium prcs- sure t o propellant tank decreased i n ascent pro pulsion system.
Veniclel Eqd;rcn?
LM-3
IM-3
IN-3
IM-3
IM-3
IM-3
IM-3
GFE
GFE
GFE
Cre
GPE
Locking pin could not be in- s e r t ed thm- bulkhead s t ruc tu re in to p a l l e t because of locat ion of hole , ~ g l e o f inser t ion and p w r l i @ t i n g .
Oxygen purge system t o be stowed in different area and more eas i ly erated locking pins us for Apollo 10 and sub- sequent missions.
Background brightness "vaahed-out" r e t i c l e lm age of cre- optical d i g m z n t s igbt during docking . o w e n p u r e 4yst- checkout li&t h i l e d .
C o m i c s t i o n a lost vhe using lightweight head- s e t md cmmmicntions c a r r i e r .
Neutral density f l l t c r and reflection frolp cornnand mod- u l e .
Meln p e r svi tch actuator
nr i tch.
Possibly caused by loose sir- lock sleeve on connector or lapmper mating of li&t- reight headset connector t o s u i t harness M d h d a p t e r .
mechanism did not cloae
Apollo
Rro ranges of r e t i c l e Apollo illumination in t ens i ty t o be provided and d i f - ierent l i gh t ing conditicna expected for Apollo 10 and subsequent missions.
Actuator mecbanizm modi- Apollo
sub sequent missions.
Airlock sleeves t o be Apollo torqued t o between 45 bod 50 inch-pounds and Lock-tite applied t o aecure sleeves t o con-
fled for ApOllo 10 Md
Re f a r e x e s
MSC-PA-R-69-2
MSC-PA-R-69-2
MSC-PA-R-69-2
MSC-PA-8-69-2
MSC -PA-R-69-2
MSC-PA-R-69-2 (Mission Rept MSC-PA-R-69-2 (Anomaly Rept No. 11
YSC-PA-R-69-2 (Misslo1 Rept MSC-PA-R-69-2 (Anonaly Rept No. 2)
UC-PA-R-69-2
YSC -PA-R-69-2
YSC-PA-R-69-2
HSC -PA-R-69-2
MSC-PA-R-69-2
.
! ...
R x s i b l e intermit tent fail- w i n SM wiring, rendezvous radar control box. or trans- ponder; possible improper switch configuration.
no. I St a t enent
None.
1
2
3
4
5
6
7
0
9
10
11
12
13
pol10 10 I
B u r s t d isc i n reaction control aystem ruptured pr ior t o f l i g h t .
Helium m i f o l d pres- sure i n reaction contm system decqyed.
Rendezvous radar trans- ponder f a i l ed t o operat temporarily .
Prinary evaporator drie out a f t e r a few minutes of operation.
Transmissions from LY 0 YHF simplex-A not re- ceived i n CM.
lBC-M)126
Crew couch s t a b i l i z e r left connected during launch.
Fuel c e l l 1 pump pack- age f a i l u r e .
Hydrogen flow t o fuel cell decayed slowly af- t e r extended hydrogen purge of fuel c e l l 1.
Automatic pressure con- trol system d i d not tul: 'lydrogen tank heaters o f f during he1 c e l l 1 Purge.
Gyro displsy coupler drift was f e l t by crew
Ground-plane radial hung up pollo 10 on guide ramp.
t r y monitor system
uls ion on s c r o l l dur- t d not deploy properly
ty lus cut through
ng pre-entry t e s t s .
recovery antenna 1 MSC~OOl26
Vehicle/ Equipment
CSM-106
CSM-106
~ ~ ~ - 1 0 6
CSM-106
CSM-106
CSM-306
CSM-106
2st4-106
:s~-106
3 ~ - 1 0 6
~SM-106
EM-106
~ ~ ~ - 1 0 6
r a t ed i n procedure#. Leak check t o be a d e
pre f l igh t checkout,
Lm-preisure helium manifold System t o be pressurize
insure leaks are detect days pr io r t o f l i g h t t o
i n fuel l e g of system A lea- t o 100 ps i a about 30 ed s l igh t ly .
MSC-00126
Insuff ic ient t r ave l of va t e r Actuator r igging proce- control c i r c u i t switch actu- dures modified t o assur a tor . proper overtravel.
Both vehicles were probably None.
f o r con!munications on simplex A. not configured simultaneously I polio 10 ~sc-00126 l i Stab i l i ze r should have been Mandatory inspection removed pr ior t o launch t o allow stroking of couch ingress checkl is t . struts i f M mbort had been required.
point added t o pre-
Phase-to-phase short , pmb- None. MaJor redesign of ably caused by breakdown of insulat ion i n hydrogen pump. required.
hydrogen pump vould be
Extended purge created lov temperatures on regulator and consequent regulator leakage.
ydmgen purge.
MSC-00126
Pressure transducer s h i f t re- Extended hydrogen purge su l t ed from cold soak during not to be performed on
subsequent f l ights . extended purge.
D r i f t r a t e s i n pos t f l i gh t k. t e s t s w e r e not indicat ive of reported performance.
poll0 1 t Cover deformcd because of d i f f e ren t i a l pressure. Cover contacted and slowed tape r ee l .
Ikulsion cause of
had hardened be- chelnfcsl react ion.
WC-00126
Msc-00126
Msc-00126 MSC-02417
F- I 2
Corrective Action
Membrane device in s t a l - led on va te r gun fo r Apollo 11 and subsequent spacecraft. Hydrogen separator i n s tn l l ed in water system f o r Apollo 12 and subsequent spaced
- a0 . 14 -
15
16
17
18
19
20
21
22
23
24
-
:.:issions R ~ f e r a x e s
Apollo 10 MSC-00126
A r A 0 m l Y Statenent
otable water contained as.
Excess lubricat ion from 0- ring p a r t i a l l y clogged gun.
Incorrect f i t t i n g in s t a l l ed 3n vent p r io r t o f l i g h t .
low from water gun ap- eared t o be l e s s than orma l fo r about 2 hour
c ra f t .
changed t o insure tha t excessive lubricant is not usea.
fomed on Apollo 11 and uMel would not vent r i o r to LM separation.
Lnslllation vent holes vere >bstructed.
hermal coating cam f f forvard hatch when M cabin vas pressurize
Evaluation showed tha t pol lo 1 insulat ion is not nec - essary. Single l aye r of H - f i l m tape applied t o hatch ablator fir Apollo 11 and subsequen spacecraff. I
aunch vehicle engine arning indicators op- ratbd intermit tent ly uring p re f l igh t t e s t -
i g i t a l event timer umped 2 minutes. A t ther times! tens+f- cconds f a i l e d t o 8d- mce.
ng - ;purious noise input prob- ably caused 2 4 n u t e Jump. Pens-of-seconds problem VBS :awed by contamination (paint lhkes from un i t s wheel) pre- renting e l e c t r i c a l contact be- tveen t a b and brush.
x k i n g r ing charge , lder not captured by etention spr ing .
s -pcec ran .
Screening t e s t develop- ed.
i e l c e l l 2 e x i t temper L u r e osc i l l a t ed .
k t en t ion spring design mar- g o a l .
mcb heat s t r u t lock- It hanhle in locked )s i t i on .
ecovery flashing l i g b t !aaed t o operate a f t e r mding.
Improved retent ion pollo 10 f f iC-001Pb method t o be used for Apollo 15 and subsequen spacecraft.
ig ine pitch giubal rive actuator hi1 in- Lcation received.
'Jehicle/ Equipnent
EM-106
CSM-106
CSM-106
CSM-106
CSM-106
CSM-106
CSM-106
CSM-106
SM-106
:St4-156
m4
Caase
Oxygen from pressure system and hydrogen from fuel ce l l s .
MSC-00126
:old solder Joints . h i t s screened fo r k l o 101 %C-00126 IApollo 11 and subseauen
pollo
pollo
I I O U
MSC-00126
Jnde tedned .
spring i n locking mechanism .mproperly in s t a l l ed a f t e r mdiflcation.
Phermally-induced e t r e s res xtveen the Rnah tube and i t s encspsulant caused the noah tube t o crack.
\n unconrnnded gimbal move- ment probably occurred due t c idlure of t he spring-loaded wake t o en- a f t e r re- m m l of dr ive s i w .
Block 11 retrof i t secon dary coclant bypass valve (Block I valve poppet) used on Apollo
Mandatory inspection
pollo ll
AOB changed so t ha t MSC-02623
11.
p point added t o manuhc- lturing process.
light is t o be operated o n 4 i n lov-flash-rate ,mode during descent.
Brake mechanism was re- designed. Time alloved for uncommnded gimbal movellrnt without c a u - ling a fail indicat ion w a s increased. c
i \
F- 13
A..or.aly P O . Sratezezt
25 Master alarms and de- scent propellant low- l eve l indicat ions durin descent phasing maneuw
26 S-band backup down-voic received from LM durlne revolution 13 was un- usable.
27 S-band s teerable antenn did not t rack.
28 Optical system problems a . Contamination on re i c l e of al lgnmnt opt l - ca l telescope.
b. Reticle dimmer con- t r o l required mar.ual holding in bright posl- t i on . c. Stars could not be seen six s t a r diameters from center of r e t i c l e .
29 Drinking water containe gas.
30 Cabin noise l eve l high.
31 Heater l i g h t on oxygen purge system d id not come on.
32 Recording of LM low-bit r a t e PCM data in CM ceased before all data received.
APOTLO 10
Cause Corrective Action
First master alarm and lov- level indication were prob- ably caused by a gas bubble around t he propellant low- level sensor. A second spacecraft. l i tarm probably resul ted from M intermit tent f a i lu re in the master alarm and pro- pellant-level c i r cu i t s .
3perator e r ro r within Gold- None. stone s t a t ion .
Descent propellant low- l eve l indicator removed from master alarm for Apollo 11 and subsequen
hack mode switch was prob- None. ably inadvertently switched to OFF.
a. Contamination could have a. Ret ic le and prism entered through air &ap a t were cleaned when sun- interface of mirror and t e l e - shade m a i n s t a l l ed on scope housing subsequent t o prelaunch cleaning.
Apollo 11 spacecraft. Saw procedure t o b e used fo r subsequent sps craft.
b. Operation normal. b. lone.
c . Prism vas possibly con- C. S . w as ( a ) . Laminated during tine?. in- s t a l l a t i o n of telescope sun- shade.
Probable source of gas vas n i t r o F n pressurant i n tank nnd air entrapped i n water hose, gun and connecting plumbing. Bacteria f l l t e r (which helps remow gas) waa not used on t h i s mission.
Prelaunch procedures changed t o include s e r - vicing water hose and connecting plumbing.
Glycol pump. Ear plugs provided for sleep periods. Mufflex added a t ou t l e t of punp for Apollo 1b and sub- sepuent Spacecraft.
Jnknovn. Failure could not None. Operation vi th- 3e duplicated in postflight out heaters acceptable. tes ts .
3l communications reconfig- None. wed from voice and data mode to ranging before completion >f dump.
dost probably caused by s t a t i c f r i c t i o n from contam- analyzed and no dis- tnation tha t m y have been Lntroduced during rebuilding.
Apollo 11 gyro h i s to ry
crepancies found.
- issions
0110 11
0110 11
ollo 11
0110 1(
0110 11
0110 9 sollo 11
0110 1(
0n.o 1c
0110 1(
-
MSC-00126
MSC-0012b
MSC-00126
MSC-00126
MSC -001 26
MSC-00126
MSC-00126
MSC-00126
MSC-00126
F- 14
so.
91
35
36
AnOmalV
Statement
Instrumentation d i s - crepanci es :
a. RCS chamber pres- sure svi tches f d l e d closed. b. Indicated glycol temperature vns zero vhen pump svi tch V a s i n pump 2 position.
c . RCS mtdiOld pres- e w e indicat ions er- roneous . d. Temperature mensure ment of thermal shield f o r radioisotope therrm e l e c t r i c generator CMk Incorrect. c. Descent oxidizer tank ullage pressure indicat ion in cabin vas zero p r io r t o descent engine f i r i ng .
Cabin pressure dropped rapidly aqer LM j e t - t ison.
Unexpected carbon di- oxide l eve l s i n cabin.
a. Probably caused by resi- due uuder w i t c h dlapht.sgma.
b. Possible broken jumper across pump svi tch contacts. or incoaplete contact in pump 2 svi tch position.
C . Possible defective con- nections and cal ibrat ion s h i t t s .
d. Probable broken Vire. f a i l ed transducer, o r baro- svi tch failure.
e. Probably f au l ty trans- ducer or v i r ing betveen t rans- ducer and cabin d i s p l q .
Hatch l a t ch f a i l ed because tunnel could not be vented p r io r t o Je t t i son (see item
Probable @eater-than-pre- dicted l i thium hydroride car t r id@ perfornance vnri- ations.
Abort guidance mode control s v i t c h wm inadvertently cy- cled, folloved by nn incor- r e c t output of the yav rate p. In react ing t o yav r a t e gyro problem, the guid- ance mode control w i t c h vu t ransferred t o A m . maul t i45 in h i @ ra t e s .
Semor uncovered by gaa bubble.
F i b v w binding i n magazine b e c a u e of dsaaged film sd- vnnce mechanism. LWre motor bet- overloaded and fai led.
Marginal c l e u m c e betveen camem and mngarine required extrm cwe to obtain proper rlignment.
U.gbzine inter lock micro- avi tch fai led.
a. None.
b. None.
C . C r i t i ca l measuremen' t o be instrumented v i th improved transducer on Apollo 15 nnd subscpuen' spacecraft. d. Inetrumentation v i r . ing t o be checked after f i n d in s t a l l a t ion .
e. None.
None required.
1;).
Predictions t o be mod- eled around more r e n l i s t i c operational char=- t e r i s t i c c .
Crev br ief ing.
None. Propel lants v i l l be s e t t l e d vhen ascendii R P m l m u surface.
PrcfligPt inspection t o be impmnd. h r se t o bt chsnged fro6 1.6 amp t o 1.2 q.
Magazines t o be checked for proper dearaaccs.
High r e l i a b i l i t y nr i tches in s t a l l ed in c-ras for Apollo 11 and subsequent missions
W 1 k cborm f a i l e d t o omrate v i t h one mag
37
38
39
az in i . I
Lsrge a t t i t ude excurd aions occurred at stag. ing.
Mnster dam and ascent propelleat lov-level i n dicntion during first =cent en&ne f i r ing .
LH 7 0 4 camern :topped
h l CM 16- c u r a ceured I to operate in pul.e
mm 2
Caus l Corrective Action
- H i S S i I
,pollo
4pollc
Rpollc
ipollc
pol lo
pol lo
pollo
pollo
I_
-
References
MSC-00126
MSC-00126
MSC-00126
wc-00126
MSC-00126
Msc-00126
~sc-90126
MSC-OOl26
F- 15
Caus l
Leakage due t o contamination induced f a i l u r e of so lenoid c o n t r o l valve.
Probable open on te rmina l board i n h e a t e r c i r c u i t . In- Dperative condi t ion e x i s t e d during countdown.
I n t e r m i t t e n t t e d n a l board connection.
Probable shor t due t o punc- tured i n s u l a t i o n .
c
Correc t ive Action Xission
F i l t e r s i n s t a l l e d i n Apollo 1 Apollo 1 2 and subsequenl spacecraft.. Aitrogcn f a c i l i t y c l e a n l i n e s s more c l o s e l y c o n t r o l l e d .
Launch s i t e test re- Apollo 1 quirements changed t o spec i fy amperage level t o ver i fy t h a t bo th tank h e a t e r s a r e opera t iona l .
Records researched and Apollo 1 no ques t ionable termi- i n a l boards used i n c r i t - i c a l c i r c u i t s on sub- sequent s p a c e c r a f t .
Insure t h a t remaining Apollo 7 u n i t s have proper ly Apollo @
Apollo 9 routed v i r e s . Apollo 1
An0r;iv
Probable f a u l t y capac i tor i n None. No previous alarm c i r c u i t . m e h i s t o r y of capac i tors .
Py-rotechnic shock. None requi red o t h e r than procedures s t a t e d
. for Apollo 9.
No. I Statement
Apollo 1
f a i l - A p o l l a 1
Apollo 9 Apollo 1 Apollo 1 Apollo 1 Apollo 1
1
2
3
4
5
6
r
1
I
.O
.1
.2
h n s d u c e r nega t ive ly b iased :ecause of change i n h e a t e r ' e s i s tance v i t h i n flow sensor :[email protected] -
Nitrogen pressure de- cayed i n secondary ser - v i c e propulsion engine ac tua t ion system.
Heater element i n ox- ygen tnnk 2 inopera t ive
Automatic c o i l of CM RCS minus yaw englne valve responded e r r a t - i c a l l y t o f i r i n g comman
Electroluminescent seg- ment on ENS numeric d i s play vas inopera t ive .
3xygen flow r a t e master a l a r m s during i n i t i a l L p r e s s u r i z a t i o n .
Propel lan t i s o l a t i o n valves closed at CSM/ $-IVe separa t ion .
None. Indica t ion o f o v g e n f l o v r a t e w a s lover tha. normal.
. .- -
Tie-wrap knots became u n t i e d on forward hea t s h i e l d mortar umbi l ica l lanyard.
Primsry v a t e r l g l y c o l evaporator o u t l e t tem- pera ture d i d not s t a y v i t h i n normal limits.
Serv ice module d i d not s k i p out. of e a r t h ' s at- mosphere.
Fue l c e l l 2 e x i t tem- pera ture p e r i o d i c a l l y d is turbed .
Vehicle/ Equipment
CSM-107
CSM-107
CSM-10'1
CSM-107
CSM-107
CSM-107
34-107
3SM-107
_ -
3SM-107
:SM-107
XM-107
:SM-107
)dor resembled burned vire . m u l a t i o n ; hovever, It vas r o b a b l y caused by outgassing 'rom hatch a b l a t o r m t e r i a l . Higher a b l a t o r temperatures lay have been experienced be- !ause of removal of ha tch iu te r i n s u l a t i o n . 1
Brief c revs . kpollo 1:
pol l0 1: i" h o t s improperly t i e d .
,u.ator f a i l e d .
81Oshing e f f e c t s .
lot det r imenta l ,
References
Msc-00171
Msc-00171
MSC-00171
Ms c -00171 MSC-02417
MSC-00171
ISC-00171
MSC-00171
MSC-00171
MSC-00171
MSC-00171 MSC-03460
MSC-00171 EC-03466
MSC-a2426
F- 16
m
0 . - 3
b
5
6
.7
L8
19
20
21
22
23
24
Anomaly S t a t e n e n t
s s i o n timer stopped.
c l i n t h e descent pro. t s ion system m e l l h e - um heat exchanger w a s m e n by helium f lovin i rough t h e hea t exchant , causing h i & f u e l ne pressure when hea t aked back from t h e en. ne a f t e r landing.
b i n i n d i c a t i o n of c a r n d ioxide p a r t i a l p re r e high a f t e r ascent .
mmunications d i f f l c u l m a i n t d n u s i n g s t e e r
l e antenna.
mputer alarms occur- !d dur ing descent .
b i n depressur iza t ion imc longer than expect
l e c t m l d n e s c e n t B e g e n t on abort guidance ystem e n t r y and d i s p l t ssembly VBS i n o p e r a t i ?
reakup of voice trans. i s s l o n occ,urred durini x t r a v e h i c u l a r a c t i v l t :
cho rece ived dur ing p l i n k m i c e tranamis- ions.
iata s t o r a g e e l e t t r o n -
'ecord properly. C S MSrmbly did O O t
hob on engine - c ir w i t b reaker WM broke
! h n m t chnmber presaur w i t c h had d o v respon ;o Jet dr1-r Compsnda
c h i c l e / Iu ipzent
M-5
H-5
H-5
N-5
M-5
LM-5
LM-5
LM-5
M-S/MSRi
IM-5
IM-5
w-5
Correc t ive Action
v s l l a b l e .
Lmultanmus vent ing o f pro- Ellant and s u p e r c r i t i c a l he- Lum tanks.
ondensate got i n t o sensor a w i n g erroneous i n d i c a t i o n s .
e h i c l e blockage and m u l t i - a t h i n t e r f e r e n c e .
:xecutive overflow alarma, ,aused by automatic mul t ip le ,escheduling of t h e same Job. 'he mult ip le rescheduling vas : a w e d by counter i n t e l l l l p t s k o m t h e rendezvous r a d a r :oupling d a t a u n i t .
Iepressur iza t ion t h r o m bac- : e r i a filter requi red more :imc than predic ted .
Probable component or Vir lng failure.
Probable inadver ten t low set- t i n g of s e n s i t i d t y control..
Inherent i n communicationr system.
Probable open i n t iming s i g - nal r e t u r n l i n e and voice s i s a l l i n e .
Knob uns probably broken by impact of owen p u r e sy.- tern dur ing EVA p r e p a r a t l o m .
Probeble p a r t i c u l a t e contam- i n a t i o n i n e t c h inlet pas- sage.
l i u m so lenoid va lve b e c losed p r i o r t o
e l vent ing and opened mc t ime l a t e r .
s i n tank vent l i n e l o c a t e d on Apollo 1 3 d subsequent space- aft .
berational procedures I b e changed t o mini- ze v e h i c l e blockage id mult ipa th condi- .om.
tndezvous radar coup- d ~ g d a t a u n i t counter i t e r r u p t s no t processel l ing Luminary 18 pro- rum on subsequent m i s - tons. Not as much imputer t i m e r e q u i r e d m descent monitoring.
a c t e r i a f i l t e r not use n Apollo 12 and subse- uent spacecraf t , re- ucing decompression ti
o r e comprehensive pre- aunch t e s t i n g requi red
r i e f crevs.
-link voice i n h i b i t e ur ing per iods of upl in o i c e transmission.
ire harness at conncc- or mapped wi th t a p e t #revent flexure damage sn Apollo 12 and Sub- equent s p s c e c r a i t .
' i r c u i t b reaker guards n s t d l e d on A p o l l o 12 uld subsequent space- :raft.
lrlcf c r w s t o recog- iize and handle similu roblcms.
- issiocs
0110 11 0110 12 ion0 1:
0110 11
,0110 11
roll0 11 10110 1; ,0110 11 ,0110 1:
mall0 1
poll0 1
pollo 1
p o l l 0 1
pol lo 1
p o l l 0 1
,poll0 I
ipollo I
3eEerer.crs
:~sc-ool71
MSC-00171
MSC-00171
51sc-001n
MSC-00171
MSC-00171
MSC-00171
MSC-00171 -
MSC-00171
MSC-00171
MSC-00171
MSC-00171
.
F- 17
/
Cause Correc t ive Action Missions . References iio. S t a t e a e n t
Reaction c o n t r o l system warning f l a g s observed for t h r e e engine pairs.
Lunar sur face t e l e v i s l o camera cable r e t a i n e d c o i l e d shape.
Hating e l e c t r i c a l con- nec tors from remote con t r o l u n i t t o por tab le l i f e support system V(LS
d i f f i c u l t .
Closing of sample re - turn conta iners vas d i f
25
26
27
28
29
Probable erroneous caut ion /None. No h i s t o r y of and varnlng system or d i s - s i m i l a r f a i l u r e s . play f l a g opera t ion caused by i n t e r r u p t i o n of 28 Vdc sup- p l y or o s c i l l a t o r f a i l u r e .
Memory is inherent charac te r - Deployment geometry t o i s t i c o f cab le . be changed.
Male connector could not b e Male connector rede- firmly grasped m d a l igned . signed.
F l i g h t conta iners had not been subjec ted t o repeated Closings (LS had t h e t r a i n i n g conta iners . and l u b r i c a n t had been removed from l a t c h l inkage dur ing cleaning.
Lubricant burnished on after cleaning.
a t e r en tered suit suit h a l f vent
Apol lo ll WC-00171
Apollo ll MSC-00171
Apollo 11 MSC-00171
RpoUo 11 MSC-00171
l -
Cacsc Correc t ive Acrior. %iss ic
f i c u l t .
1
2
3
4
5
Anox=ly ;:o. I S t a t ezent
Display/keyboard mal- functioned p r i o r t o launch - displayed all 8 ' s .
Hydrogen tank 2 heat l e e p r i o r t o launch.
Lightning s t ruck space- craft and launch v e h i c l r e s u l t i n g i n : a. Loss of n ine i n s t r u mentation measurements. b. Loss of i n e r t i a l platform reference . C . Disconnection of f u e l c e l l s .
S t a b i l i z a t i o n and con- t r o l aystem c i r c u i t breaker was open dur ing p o s t i n s e r t i o n checks.
Propel lan t and he l i t& i s o l a t i o n valves c losed at CsM/S-IVB separa t ion
R o b a b l e r e l a y contamination.
~~ ~~~
Vehicle/ Equimcnt
Fabr ica t ion process im- p o l l o proved t o minimize con- tamina t ion , sc reening procedures improved, M
malfunction procedure developed t o c l e a r con- d i t i o n . t
IM-5
IM-5
GFE
CFE
GFE
s t e e l / t i t a n i u m b i m e t a l l i c j o i n t .
Vci.icle/ B y d i Tier.:
CSM-108
CSM-108
CSM-108
EM-108
CSM-108
moved and rep laced . Tanks from l o t s suspec- t e d of having poor pual ity j o i n t s r e c a l l e d f o r replacement of j o i n t s .
Probable leakage through water s e p a r a t o r s e l e c t o r valve. .
ind ing incorpora ted i n
HSC-00171
p o l l o r Vehicle launched dur ing thunderstorm. s p e c i f y a l l o v a b l e mete-
o r o l o g i c a l condi t ions . Programing change made t o i n h i b i t a c t i v a t i o n of p la t form c o a r s e - a l i mode dur ing launch.
Pyrotechnic shock.
MSC-01855
MSC-01855
MSC-01855 MSC-01540 MSC-04112 supplement 8
MSC-01855
WC-01855
F- 18
h u f a c t u r i n g require- nents t o inclrde torque tes t ing of bracket.
3heck valves fo r leak- age when water tempera- ture is 150° F.
#one. Lanyard function complete before drogue b e p l o p n t .
a. Sone. Measurement not neceaaary fo r f l i g h t .
b. ! h e . Problem con- sidered t o be isolated occurrence. c. none. f i t e rna te methods avai lable f o r determining water i t y .
I
!lo.
6 -
r
8
9
10
11
12
13
14
15
16
-
Apollo 1 2 MSC-01855
Apollo 12 MSC-01855 Apollo 1L
Apollo 12 MSC-01855
KC-01855
Apollo 12
ApoUo 12 Apollo 12
A ~ O ~ O 8 Apollo 1;
quant..Apollo 1
Ar.omalv Statement
peration of S-band hie ain antenna in narrov- 'eam mode resul ted i n ow signal strength on everal occasions.
miscrepancy in actual measured) and calculat mxygen usage.
M crew saw st rap-l ike vl ter ia l in v ic in i ty 01 ,M/SLA interface Jus t , r i o r t o docking.
n&ar posi t ion of op- i c s shaft fluctuated n zero opt ics mode.
'lndows were contamin- .Led.
iIF recovery antenna 2 i d not deploy properly
oimmnd module RCS ox- dizer i m l a t i o n valve ould not remain closed ur ing postf l ight oper- t ions.
etent ion bracket fo r x y p n hose cBmc loose uring landing.
ood preparation unit caked a f t e r hot water ispensed.
'oruard heat shieidmor ar umbilical lanyard 'BI severed.
nstl=uu.entation discrep nc ie s : I. RCS quad D helium m i f o l d pressure in&- at iona erroncouII. ,. Sui t pressure t rans . w e r indicated lov.
. Potable water quant
I
t y da t a HTatiC. 1
Vehi clef E t u i y e n t
CSM-108
CSM-108 ' I
CSM-108
CSM-108
CSM-108
csn-lo8
CSM-108
CSM-lo8
CSM-108
CSH-108
CSH-108
.ed hydrogen pressure Iecqyed.
Cause
Probable f a i l u r e of dual di- plexer or narrow-beam compar- itor congonent.
Leakage from 900-psi oxygen system within service module.
Material was similar t o loost pieces shown on Apollo 10 photos.
Possible motor drive ampli- f i e r module m a l h c t i o n .
Rain water, residue from launch escape system engine, and outgassing of s i l i cone oils from window seala (hatch only).
Rdhesive substance probably neld protect ive f l a p over p u n d plane radials .
Demaged bellows. probably re- su l t i ng from pressurizat ion of system with i so l a t ion valves closed.
Bracket not properly bonded t o panel.
Tuo valve O-rings damaged from. par t i c l e contamination.
Probably broken by drogue s t e e l cable r i s e r when drogue was deployed.
a. Probable wedrening of s t r a i n e g e bonding.
b. Transducer i n t e rna l ly contaminated v l t h oickel- p l a t ing pa r t i c l e s . c. Stain found on potentiom- e t e r res is tance vafer . no evidence or moirture o r urine contamination of measuring system components .8 on Apollo 8. d. Robable leak in pres- sure transducer diaphragm.
Corrective L c f i C n :!iss:or.: Rc.r'?rer.cis
sidered not detrimental
sign deficiency.
vent rain water leakage b. Hatch window cnvity purge pr ior t o f l i g h t . C . Insulat ion material .elmoved from between in ier and outer hatch win lows.
Itructions t o wswe r e ma1 of adhesives and >roper deployment of .adials.
Apollo 1 '
.
F- 19
A..oaaly ~
No. S t a t e z e s t 17 IPanel 2 mission c lock
La
19
!O
!1
!2
’3
?b
25
26
27
28
29
30
tun ing fork d i s p l a y op- e r a t e d i n t e r m i t t e n t l y and clock had cracks i n face &lass.
VHF communications be- tveen CSM and LA dur ing ascent and rendezvous were unreadable.
Docking hatch flood- l i g h t s v i t c h d i d not
loperate properly.
Water came out of suit i n l e t hoses.
Cabin . ind ica t ion of car . bon dioxide p a r t i a l pre: s u r e e r r a t i c .
Tracking l i g h t f a i l e d .
MESA handle could not be r e l e a s e d from sup- port b racke t .
Hatch t h e d s h i e l d t o r n , causing p o t e n t i a l hazard t o suit.
Lov-level descent pro- p e l l a n t q u a n t i t y l i g h t i l lumina ted e a r l y .
Lunar sur face color t e l e v i s i o n camera f a i l e
16- camera operated i n t e r m i t t e n t l y dur ing ascent .
h e 1 capsule f o r rad io- i so tope thermoelec t r ic genera tor vas d i f f i c u l t t o reuove irom cask 8s- semb1y.
Thermal shroud on pas- s i v e seismic experiment would not l i e f l a t end l d . n a t i ons separa ted .
Cold-cathode ion g a p Hould not remain up- r i g h t . I
Vekicle/ i’quip5er.t XSM-108
:SM-l08
IM-6
IM-6
m-6
LM-6
IM-6
m-6
W-6
GFE
GFE
ALSEP
AISEP
AISEP
Cause Correcr ive b c t i o n
Probable c rackea s o l d e r j o i n t Nev mission timers de- a s s o c i a t e d v i t h cordwood con- veloped for Apollo 13 s t r u c t i o n . Manufacturing and subsequent space- process induces stress i n t o c raf t . Clear pressure- g l a s s . s e n s i t i v e tape placed
over g l a s s .
Improper squelch s e n s i t i v i t y Brief crews and u s e con s e t t i n g i n CM. Improper use munications c a r r i e r hes of l i g h t v e i g h t headset i n CM. sets dur ing c r i t i c a l mi
s ion phases.
I n s u f f i c i e n t plunger t r a v e l . Plunger t r a v e l in- creased.
Water bypassed v a t e r separa- t o r because o f excessive water separa tor speed.
Water s e p a r a t o r speed reduced by adding I l o v l i m i t o r t o primary litt ium hydroxide c a n i s t e r for Apollo 13 and sub- sequent spacecraf t .
Probably caused by water en- Water separa tor sump t e r i n g 8enior . t ank vent l i n e rerouted
for Apollo 13 and sub- sequent spacecraf t .
Corona i n high-voltage sec- Tracking l i g h t rede- t i o n of l i g h t r e s u l t i n g from signed f o r Apollo 13 high temperatures degrading and subsequent space- p o t t i n g compound. craft .
D-ring stuck i n r e t e n t i o n D-ring e l imina ted , and socket because of binding of loop clamped t o end of b a l l de ten t or p u l l i n g D-ring deployment cable f o r a t M angle. Apollo 1 3 and subsequer
PLSS snagged on s h i e l d dur- Shie ld th ickness in- i n g crevman egress.
s p a c e c r a f t .
c reased and diameter oi s h i e l d mounting h o l e s increased .
Lov-level po in t sensor un- Sampling r a t e increase< covered by propel lan t s losh- and d a t a averaged auto. ing . m a t i c a l l y f o r Apollo 1:
and subsequent space- c raf t .
Crev t r a i n i n g and oper-
changed. 4
Design of i n t e r l o c k switch a c t u a t i o n mech-
Image sensor vas exposed t o extreme l i g h t level. damng- a t i o n a l procedures i n g a por t ion of t h e target.
I n t e r m i t t e n t a c t u a t i o n of magazine i n t e r l o c k micro- s v i t c h contac ts . anism changed.
Binding betveen t h e contact Fuel capsule backplater sur face of fuel capsule back- reworked t o increase p l a t e and t h e l a t c h on t h e c learance for Apollo 1: cask. and subsequent missions
Effec t of 1/6-gravity g r e a t e r Laminations s p t - s e v e d than expected. and v e i g h t s added.
Cable s t i f f n e s s and e f f e c t s Different experiment of 1/6-gravity. c o n f i g m a t i o n used f o r
Apollo 13. For subse- quent missions, cab le wrap remved t o reduce c a b l e s t i f f n e s s .
p o l l o 121 HSC-01855
pollo 12’ MSC-01855
pol lo 1 2 MSC-01855
lissi0r.s [ pei.c;Dcs
pollo 7 MSC-01 55 i
poll0 UI poll0 l2 pollo 15
30110 121 MSC-01855
pol lo 12 MSC-01855
pollo 12 MSC-01855
pol lo 12 KC-01855
poll0 1 2 Msc-01855
pollo 1 2 k5C-01855 poll0 14
F- 20
Caue
Single spring c l i p on r ight- hand bag WBS not adequate fo r bag retent ion.
Magazine was inadvertently opened allowing film holder t o come out. This resul ted i n improper f i lm transport .
*,oEaly !lo. I Statement Corrective Action !<issisn!
Double spring c l i p t o beApollo 1 added fo r Apollo 13.
Film release knob taped Apollo 1 a r t e r magazine loading and crews br iefed.
-
31
32
33
3b
35
36
37
i'e+i c l e / Zqui-cr,er.t
GPE
CFE
GFE
CFE
GFE
GFE
CFE
~
mpty col lect ion bag tended t o come loose from too l ca r r i e r .
Frame counting on CM 7O-mm camera did not agree with crew count.
Sui t pressure pulses were f e l t by IMP during ex t r awhicu l s r a c t i v i t y
Exposure counter on lu- nar surface close-up camera did not always count.
Shut ter , counter and f i lm advance act ions of 7O-mm lunar surface camera were intermit ten
EVA commicat ioos de- p-aded by tone and nois
Weigh bags cracked and t o r e when handled on lr nar surface, and when used for t o t e b a q , samples bounced out.
2 Postlanding vent vaIve malfunctioned during
(exhaust wve q u n - i d c t Vave cloaed).
p o J t h d i n g actidties
No evidence of system mal- function.
CSH-109
None.
3 Optica shaft vlgle n u c CSM-109 Itvat, in zero optics 1
counter.
Loose handle and trigger as- sunbly.
i n handle).
Thumb wheel secured by star washer and roll p i instead of spring vashe snd s e t screw.
Tone caused by interference from fan motor when micro- phone amplifier supply vol t - age was below regulator t h re s i - old of 12.5 volts. Random noise may have been caused by intermit tent open in primary winding o f amplifier trans- former.
poll0 1, t
Brief crew and improve qua l i t y control.
Apollo 1
Material (Teflon film) waa Containers made of Tet- Apollo 1 too b r i t t l e and covers were lon cloth f o r Apollo 13 not p o d d e d . and subsequent. Collec
t i on containers provide with means of c losing f r i Apollo 1b and subsequcn .
- ~
HSC-01855
MSC-01855
MSC-01855
HSC-01855
MSC-01855
MSC-01855
MSC-01855
A f i r e which ybs s t a r t ed by e l e c t r i c a l short-circui ts in t h e wiring t o the fan w t o r s inside t h e tank led t o stauc- turd fa i lu re of the tank.
The tank design WM
added, an i so l a t ion val e
an auxi l iary ba t t e ry va
and subsequent spacecm f , changed, a t h i rd cryo- genic oxygen tank m5
fo r tank 3 was added,
i n s t a l l ed on Apollo 1h
pollo 1 MSC-02680 MSC-02545
Power was applied t o the d w s when t h e valve unlock t o AOB t o insure tha t handle was pulled p a r t i a l l y handle is mond its f u l out. t r ave l before switching
on postlanding vent fan
Probable cause MS resis tance ietveen brushes and s l i p r i n g in half-speed resolver due t o are not i n uoe. mum and zero-@.
Shaft movement "vipt5 avqy"
. Cmse Correc t ive Action
I
I-lissic A-.on:2ly
!lo. I S'catenent
Probable Short i n primary uinding o f C a d s induct ion potentiometer r e s u l t i n g i n s h i f t of scan l i m i t nnd scan limit warning func t ions .
4
5
6
7
8
9
to
11
12
13
Launch s i t e tests added t o ensure proper func- t i o n s p r i o r t o f l i g h t . Procedure developed t o determine acceptab le s p a c e c r a f t a t t i t u d e s in t h e event of a s i m i l a r f a i l u r e on subsequent f l i g h t s .
i f f i c u l t y v a s experi- nced i n ob ta in ing high
i n antenna a c q u i s i t i o
t r y monitor system . 0 5 g l i g h t d i d not il- uminate a t proper time
as leaked from y s s e t - eech assembly in ard hea t s h i e l d J e t ning system and ed hole i n gusset
CS f u e l i s o l a t i o n v a l v as found open dur ing
s t f l i g h t i n s p e c t i o n .
t a b l e water quant i ty asurement fluctuated.
it pressure measure- n t was e r r a t i c .
c t r i c a l c i r c u i t in- r u p t e r leaked gas n it operated p r i o r CM/SM separa t ion .
e r c r i t i c a l helium s s u r e r i s e r a t e vas a t e r than expected
e c r e v heard a "thump g" n o i s e and saw snow akes vent ing from
uadrant 4 during t r a n s
scent b a t t e r y 2 l f u n c t i o n l i g h t il-
Zondition could not b e dupl i - 2ated i n p o s t f l i g h t t e s t i n g . Possible procedural e r r o r or momentary f a i l u r e .
'oss ib le out-of t o l e r a n c e aarts or improper sssembly.
V e t i c l e / 2quip;er.t
:SM-109
!SM-109
:SM-109
94-109
34-109
34-109
34-109
LM-7
LM-7
LM-7
-
None.
Assembly procedures i m - proved and thermal bar - r i e r added t o breech- plenum assembly.
poll0 poll0 i:
LPOllO
Talve vas miswired. Pre- . Resistance checks t o b e r l ig t func t iona l checks d i d performed i n addi t ion lot r e v e a l discrepancy. t o f u n c t i o n a l checks on
Apollo 1 4 and subsequen s p a c e c r a f t .
3 o b a b l e e r r a t i c opera t ion of transducer. S p e c i f i c ev i - ience of contamination or :orrosion could not be found. Pransducer probably c o n t w i n - ated by n i c k e l p a r t i c l e s .
\ p o l l o ipo l lo \poll0
i p o l l o
than normsl. Not de t r imenta l
vacuum contamination. 1 t e s t i n g f o r Apollo , 15 and 16 tanks.
d n M t s dur ing m
Dattery l i d being blovn o f f .
e r y were modified p o l l o 14 and subse i s s i o n s . The d e s i t h e r Apollo b a t t e r as considered safe .
F- 21
R e f e r e x e s
KC-02680 MSC-03753
MSC-02680
MSC-02680
KC-02680
MSC-02680
MSC-02680
MSC-02680
SC-02680
MSC-02680
EC-02680
F- 22
Cause
Shutoff valve leaked , prob-
dur ing bssembly or contamin- ab ly caused by O-ring damage
a ted valve meat. Leak tests were inadequate.
Aclat covering vas not suf- f i c i e n t l y d u c t i l e .
I n s u f f i c i e n t f r i c t i o n betveen mating sur faces .
Gripping compound used t o secure set screv d i d not pro- vide s u f f i c i e n t r e t e n t i o n force .
Packaging d i d not permit sat- i s f a c t o r y opera t ion i n f l i g h t
Correct:ve Action Y i s s i o m Scferenccs
Valves t e s t e d f o r both
age a t high and l o v p r e rorvard and r e v e r s e l e
sums.
Shades f a b r i c a t e d from
in forced v i t h Mylar be- improved Acls r and re-
f o r e s t i t c h i n g .
Mating s u r f a c e of bumper svaged.
Knob secured v i t h r o l l Apollo 13 MSC-02680 pin .
p o l l o 13 MSC-02680
Apollo 13 MSC-02680 Packaging method changed.
14
15
16
17
18
~ -~ Anolraly .
KO. St at enent I
Pressure i n ascent S tag oxygen tank 2 increased i n d f c a t i n g r e v e r s e l e a k
l a n k . age from manifold i n t o
Left-hand vindov shade as cracked.
-
Vehicle1 Eyd pnen t
IM-7
IM-7
Set knob c a m o f f o f i n t e r v a l t imer .
Nasal spray b o t t l e s v e r e d i f f i c u l t t o use.
Bumper separa ted fl-om 10-mm l e n s of lunar mod u l e 16-mm camcra.
CFE
CFE
Vehi cle/ Statement E q u i p e n t
Six a t tempts v e r e re - CSM-llO qut red t o - a c h i e v e dock- ing probe c a p t u r e l a t c h engagement dur ing t r a n s lunar docking.
High-gain antenna t r a c k ing w a s d i f f i c u l t sev- ersl times dur ing trans lunar coas t and l u n a r o r b i t .
Urine dump nozzle MS
o b s t r u c t e d several ti=! d u r i n g mhsion.
1 I
VHF communications be- tveen CSM and W vere degraded p r i o r t o lunar lift-off and during ren deZMu8.
&try mnitor system 0.058 liQt d i d not il- luminate at proper ti=.
CSM-110
EM-110
C S H - l l O WA
CSM-ll0
CIlUSe ~~
Most probably. e i t h e r f o r e i g r m s t e r i a l i n t e r f e r e d v i t h t h e opera t ion of t h e capture l a t c h mechanism, or t h e t r a n s l a t i o n c m Jammed.
A five- t o e i g h t d e g r e e bores ight shift of v ide beam vus poss ib ly caused by fau l ty c o a x i a l cab le connector or shock from SLR separa t ion .
Correc t ive Action
ISeveral changes were made t o prevent fore ign m a t e r i a l &om g e t t i n g i n t o t h e probe mechan- i s m . inc luding a cover , t o be used p r i o r t o flight. Also, t h e tran l a t i o n c m assembly vas modified and t e s t s v e r e added.
Connectors r e w r k e d and inspec t ion procedures t igh tened . Thermal ac- ceptance t e s t performed v h i l e antenna r a d i a t i n g and under opera t ing con d i t i o n s .
:.!is sion!
Apollo 1
kpollo 1. kpollo 1 kpOll0 1, Apollo 1
Freezing of nozzle probably Procedural changes. Apollo 1, cauped obs t ruc t ion . Differ- en purge m d dry procedures md colder nozzle condi t ions could have cawed f reez ing .
System opera t ing ne8r range Receiver AGC measure- Apollo 11 limits. ments added t o CSM and
LM t o s tudy problem. Crew t r a i n i n g expanded t o inc lude e f f e c t s of veak s i g n a l s t r e n g t h s .
Crev's vIev of l i g h t vas ob- Clear g l a s s s imula tor Apollo 1 s t r u c t e d by n e u t r a l dens i ty f i l t e r replaced v i t h Apollo 11 fi lter. s i l v e r e d f l i g h t u n i t .
F i l t e r repos i t ioned f o r e n t r y on subsequent f1ight.J.
Refersxces
Msc-04112 MSC -05101
MSC-04112
MSC-04112
mc-04112
MSC-Obl.l.2
I-- __
h a i n bus A remained en erg ized vhen main bus- s v i t c h e s vere placed i t h e "off" p o s i t i o n a t 800 f e e t .
Main bus B - b a t t e r y C c i r c u i t brenker contac vas i n t e r m i t t e n t .
Food prepara t ion u n i t leaked momentarily aft hot water vas d ispense
Rapid r e p r e s s u r i z a t i o n system requi red rechar ing i n addi t ion t o nor ma1 rechargings.
Ascent b a t t e r y 5 v o l t -
F- 23
Contacts d i d not make because of g l a s s p a r t i c l e s on contac t sur face .
S t roke t i m e of va lve assembly was s l o v because of dimen- SiOnal i n t e r f e r e n c e betveen t h e c y l i n d e r and p i s t o n at higher temperatures.
. None requi red .
Hot v a t e r explusion t e s t s conducted on Apollo 1 5 and subscquer spacecraft.
AnorAy
KO. I Statement
Crevs b r i e f e d on re - charging techniques f o r other-than-normal re- chargings.
S t r i c t e r inspec t ion and improved procedures f o r plug i n s t a l l a t i o n
6
7
8
9
10
11
.2
.3
.4
.5
.6
Apollo
Apollo usecbpollo age decreased-.
Abort conuuand va5 s e t i n computer although abor t s v i t c h had not been depressed.
I ' b-band s t e e r a b l e antenn
anding r a d a r system vi tched s c a l e s and in1
b o r t guidance system
rak ing phase.
lass cracked on d a t a n t r y and d i s p l a y 88-
functioned.
Yehi c l e l Equlpment
CSM-110
CSM-110
CSM-110
CSM-110
LM-8
LM-8
w-8
LM-8
LM-9
LM-9
GFE
of c o m t a t o r . c ra f t . and bad s v i t c h e s rep laced i f necessary.
F i l l valve v a s c losed before system was f u l l y charged. Leakage rate vas not exce8- S i V e .
Poss ib le shor t betveen p l a t e s o f b a t t e r y c e l l , s h o r t from c e l l to case , or e x t e r n a l b a t t e r y load.
Probable m e t a l l i c contamina- t i o n wi th in abor t s v i t c h mod- ule.
lndet ermined.
\pollo
lpo l lo rpo11o
M t c h i n g t o lov-sca le range nts caused by t u r n i n g on ra- t o enable holding s y s lar too soon. I n i t i a l s l a n t in high-scale vhfle i w g e reading vas caused by antenna p o s i t i o n 1. side lobe lock-on. s c a l e switching enabl
in pos i t ion 2. P o s i t 2 automat ica l ly s e l e c t e at high gate.
Wiring modi f ica t ion
'ailure could have been Design, manufacturin :aused by any of 27 coupon- !nts i n t h e +b-volt l o g l c mer supply. t h e sequencer. quate. No c o r r e c t i v e )r t h e i n t e r c o m e c t l o n s be- a c t i o n required. :veen t h e tvo modules.
' o ss ib le i n t e r n a l stress i n Clear p l a s t i c tape a $ass. improper mounting, or p l i e d t o g l a s s s i m i l a r $ass vas i n a d v e r t e n t l y h i t . t o mission t i m r window
r r a n s i s t o r i n s h u t t e r c o n t r o l None. Screening and : i r c u i t VBS s>orted, caus ing tests considered ade :ontinuous s h u t t e r opera t ioQ md t e a r i n g sprocket ho les i n shut te r c u r t a i n .
t e s t i n g and i n s t a l l a t i o methods considered ade-
References
MSC-04112 MSC-05242
MSC-all2 MSC-05814
Msc -0411 2 MsC-Ob751
S C - 0 4 l l 2
wc-01112 MSC-05257
SC-04112
(sc-00171 Isc-04u2 ISC-07505
8C-04112
ISC-04112
KC-04112
6C-04112
F- 24
Aionaly Vehicle/ Ro . S t a t e z e n t Equipment
17
18
L9
?O
?1
22
2 3
24
25
26
27
28
Lunar Module P i l o t ’ s r i g h t glove pul led t o the l e f t and down dur- ing‘ the second EVA.
n te rva lometer double- y c l i n g occurred 13 imes out of 283 exposur
olmrmnications v i t h Com- nder v e r e i n t e r m i t t e n t i
CFE
G F E
!S.
GFE
c t i v e seismic exper i - A U E P e n t t h ~ m p e r misfired i v e times.
ransmission of operate- s e l e c t conmvrnd t o supra- hermal ion d e t e c t o r r e -
s u l t e d i n noisy d a t a f r o hree experiments.
unar p o r t a b l e magnet- meter c a b l e vas diffl- i c u l t t o rewind.
: e n t r a l s t a t i o n 12-hour .imer pulses d i d not , c c k after i n i t i a l ac- :i vat ion .
a# i n t e r m i t t e n t .
Long-period v e r t i c a l s e i smome t er o f passive lseismic experiment was uns tab le vhen operated with t h e feeaback f i l t e lin.
Active seismic exper i - ment geophone 3 data ‘showed i n t e r m i t t e n t sp ikes t o of f - sca le hig dur ing h igh-b i t - ra te l i s t e n i n g !node.
S u p r a t h e d ion detec- tor d a t a vss i n t e r m i t - t e n t l y erroneous.
ALSEP
L
U E P
Charged p u t i c l e lunar ALSEP envlronment experiment d y z e r B d a t a l o s t .
A p o ~ 14
Cause Correc t ive Action
Glove wris t -cont ro l cab le system d e s i w inherent ly al- lows glove t o t a k e various n e u t r a l pos i t ions .
Intervalometer responded t o random pulses from motor cur- ren t .
Zondition was correc ted vtien : o n s t a t wear garment e lec- t r i c a l adapter VBS replaced J i t h spare u n i t . No abnormal i t ies found p o s t f l i g h t .
Se lec tor s v i t c h d i a l may not lave been h e l d i n p o s i t i o n by i e t e n t , and f i r i n g switch may lave been contaminated by dus
Probable a r c i n g o r corona 6 i t h i n suprathermal ion de- t e c t o r equipment p r i o r t o i u s t cover r e m v a l .
e r a t i o n p r i o r t o dus t
No provis ion f o r locking r e e l J u r i n g rev ind . Gripping r e e l and crank was difficult with gloved hand.
Yechanical s e c t i o n of timer did not d r i v e switches. Loss of tiprr hss no adverse e f - f e c t on experiments.
Probable i n t e r m i t t e n t opera- t i o n of a component i n t h e w t o r c o n t r o l c i r c u i t .
None. Sa t1 s fac tory d a t a obtained by opera. t i n g experiment i n f i l l o u t mode.
Probable open in posit ive-. None. going diode-wired t r a n s i s t o r i n t h e logmrithmic compressor f o r geophone 3.
Probable i n t e d t t e n t com- ponent o r vire connection re- s u l t i n g in M i n t e r m i t t e n t f a i l u r e of t h e start r e s e t pu lse f o r t h e positive log AfD conver te r c o n t r o l l o g i c .
Probable sbor t t o ground i n t h e m a l y z e r B power supply filter, t h e analyzer. or t h e in te rconnec t ions betveen t h e two.
, Apollo 15 is - 1 ~ mission for aper j ment .
. Erperlmcnt was not c a r r i e d after Apoll
- Xssion
pollo 2
?OllO 1
M l l O 1
10110 1
?on0 1
? o n 0 1
10110 1 ,0110 1
?on0 1
pollo 1
pollo 1
pol lo 1
pollo 1
~~
References
Msc -04112
MSC-04112
MSC-Okll2
?“fSC-O4ll2
MSC-04112
Msc-04112
MSC-04112
%C-04112
mc-04112
MSC-04112 MSC-07638
MSC-&ll2
SC-04112
,
t
c
F- 25
Cause
1
Correc t ive Action - NO.
1 -
2
3
4
5
6
7
8
9
.O
U
L2
-
Latching magnets may have been p a r t i a l l y degaussed dur- ing preflight t e s t s by a p p l i - c a t i o n of r e v e r s e vol tage t o c o i l s .
I n s u f f i c i e n t septum compres- s i o n . Septum r e t e n t i o n i n - sert vas loosened vhen cap w a s removed.
Loose s t r a n d of v i r e v i t h i n delta-V t h r u s t s v i t c h prob- a b l y caused a s h o r t t o ground
Input f i l t e r capac i tor i n lover-equipment-bay mission timer vas shor ted .
Instrumentation problem. Exact cause not determined.
Cable probably Janmed in boom housing dur ing r e t r a c - t ion.
Ar.onaly S t e t e n e n t
Magnetic l a t c h i n g ?orc t e s t s performed p r i o r t o n i @ t f o r Apollo 11 and subsequent s p c e - c raf t .
Shim added under i n s e r shoulder and i n n t a l l a - t i o n torque increased for Apollo 16 and sub- sequent spacecraf t .
Nev screening proce- dures used f o r c r i t i c a s v i t c h e s on Apollo 16 and subsequent s p c e - c raf t .
Fuses added t o u n i t s f o r Apollo 16 and 17 spacecraf t .
None. I s o l a t e d c a s e and o t h e r measurements a v a i l a b l e .
The f o l l o v i n g changes vere made f o r Apollo 1( 1. The mechanism vas modi A ed . 2. A proximity s v i t c h vas added t o i n d i c a t e r e t r a c t i o n t o wi th in 1. f o o t of full r e t r a c t i o i 3. A thermal-vacuum t e s t m s added.
Serv ice module r e a c t i o i c o n t r o l system propel11 i s o l a t i o n va lves closei
INone. I s o l a t e d case. if problem r e c u r s , po- t a b l e v a t e r tank v i l l f i l l vhen v a s t e v a t e r It& is f u l l .
Water panel ch lor ine indec t ion p o r t leaked.
Se iv ice propulsion sys. t e n t h r u s t light il- luminated vhen no en- g ine f i r i n g conrand vm present .
I n t e g r a l l i g h t i n g c i r - c u i t breaker opened.
Bat te ry r e l a y bus v o l t - age reading vas lov (13.66 v o l t s versus 32 v o l t s 1.
Yass spectrometer boom d i d not fu l ly r e t r a c t 5n f i v e of t v e l v e oc- cas ions.
Potable v a t e r tank r a i l e d t o r e f i l l .
?anel 2 mission tierr stopped.
Ine main parachute c o l - Lapsed at 6000 f e e t al- t i t u d e .
Data recorder t a p e de- t e r i o r a t e d .
Seconds d i g i t of d i g i t a w e n t timer became ob- scured.
:rev restraint harness lame a p a r t on center md r i g h t couches.
Vehicle/ F-quipen
CSM-112
CSR-112
CSM-112
CSM-112
CSM-112
CSM-112
CSM-112
CSM-112
CSM-ll2
CSM-112
CSM-112
CSM-112
Check valve betveen f u e l c e l l and v a s t e tank dump l e g leaked. A small piece of w i r e vas found betveen poly- mer umbrella and s e a t i n g sur- face .
Probable i n t e r m i t t e n t com- ponent vhich hea led i t s e l f .
Rav f ie1 expel Ied dur ing de- p l e t i o n f i r i n g became igni ted and damaged t h e parachute r i s e r mnd suspension l i n e s .
Scratched recorder heads damaged t a p e ,
Elongation of idler gear bear ing p o i n t s a l loved s h a f t t o tilt and caused gear t o scrape p a i n t from number vheel.
Plug-and-cap assemblies t h a t a t t a c h r e s t r a i n t harnesses t o couch seat came a p a r t .
None. Time can b e ob- t a i n e d from o t h e r t i m e 2 o r Mission Control Cen- t e r .
Propel lan t load b i a s e d t o provide s l i g h t ex- cess or o x i d i z e r . Ro. p e l l a n t d e p l e t i o n f i r i r e l imina ted . Suspens lor l i n e connector l i n k ma- t e r i a l changed.
Removable head covers pro\<ded t o prevent handling damage during i n s t a l l a t i o n .
Units inspec ted v isua l1 for signs o f vear and p a i n t f lakes .
Thread locking s e a l a n t used t o prevent unecrei i n g o f p lug and cap.
- Yissioi
.po l lo 1
.po l lo
.po l lo
.po l l0
.po l l0
p o l l 0 :
-
p o l l o :
p o l l o :
p o l l 0 :
pol lo : p o l l o :
pol10 1
p o l l o I p o l l o 1 p o l l 0 1
pollo 1 p o l l o I poll0 1
poll0 1
p o l l o 1 p o l l o 1 p o l l o I
pollo I
-
References
HSC-05161
MSC-05161
MSC-05161
HSC-05161
MSC-05161
MSC-05161
MSC-05161
MSC-05161
MSC-05161 MSC-05805
MSC-05161
HSC-05161
MSC-05161
F-26
Anonaly 1kO. Stetoxent
13
L4
15
16
17
.a
.9
!O
11
2
3
uit breaker supply- main bus A pover t o
t e ry charger could be opened manually ing postf l ight t e s t i
l e - a r m p i w t pin fo -A shutoff valve of
n oxygen r e p l a t o r
o p t i c a l - d i g m e n t f e l l off stovage during landing.
r lg lyco l pump d i f - en t in l pressure flu
d a f t e r cabin de- ur izat ions fo r s t a A and second EVA.
e r separator speed reased during cabin ressurlzat ion fo r
tMdup EVA. t a t e r gunlbacteria fll- er w i c k disconnect roke. 1 .
errupt ion of S-bend erable antenna track. p r io r t o povered de.
n t . cent engine control m b l y c i r c u i t bredel open when checked
e r lunar module seps. bat ion.
Vehicle1 E q u i p m t
CSM-112
CSM-112
CSM-112
CSM-112
CSM-112
CSM-112
LM-10
LM-10
w-10
w-10
w-10
-
a w w
Ca-ise Corrective Action
A l/b-inch vasher vae found i n the ducting a f t e r t h e f l i g h t . The washer could nave drifted in end out of Lhe fan ou t l e t during flight.
:ondeneation ya6 probably present on the eyepiece vin- iov and on prisms i n the re- movable eyepiece.
Possible contamination be- Ween dip-rings and thumb wheel resolvers in a t t i t ude set control panel, or con- tamination of e i t h e r of tvo "golden-g" relays i n u r o nlc display aa- display coupler. replaced on Apol
r e s u l t of rc- ion of a l l devic
ed in s t ab i l i za t ion a n t r o l system.
:orrosion on indicator stem prevented operation. Cor- rosion could have been caused ,y sea water, urine o r s w a t .
Improper shimming alloved pivut pin t o come out of one side of cam holder. Pin f a i l ed i n single shear and sending. hcking pin did not engage iecause the ramp vhich moves ;be pin in to the locking posi :ion vad gouged.
it checks used t o
d crew checkl is ts d t o include ve r i on of la tching p i
:ondenantion on vater lglycol lensing lines froze and sub- Limed at cabin depressuriza- :ion. Tbis froze t h e f l u i d in t he lines. causing the in- i icat ions. :ondensation on outside of Line betveen n t e r separator pitot tube and vater manage- Dent system froze and sub- Lfmd at cabin depressuriza- tion. Thin froze the vater Ln the line. causing the sep- w a t o r t o slov down because ,f excessive n t e r .
Improper stovagc cawed ex- cessive force t o be applied to quick disconnect by bend- Log hose.
e and cownand module. o additional comec- ive act ion taken (see poll0 14).
,reoker van probably left r. 'pen by crev.
- '?lSS?O?. - Rpollo L p O l l O : \poll0 2
pol10 1
pollo 1
pol10 1
pol10 1
pol10 1
poll0 1
PO110 1
pollo 1
,0110 1: 10110 1; 10110 11 iollo 1' m l l 0 I'
P
Xeferencas
MSC-05161
MSC-05161
MSC-05161
MSC-051
MSC-05161
NSC-05161
sc-05161
~sc-05161
MSC-05161
ISC-05161 Ex-07 505
BC-05161
.
Cause
Probably caused by R4J from t e s t mode f a i l buffer momen- t a r i l y turning on t e s t mode f a i l driver. This could have latched t h e wter alarm and abort guideace sytem varning l i gh t on.
Corrective A:tion
Lov s ide of input t o buffer grounded t o sup- press noise feedback.
8
m e most probable cause vas M open i n t h e rendezvous ra- lar signal re turn l i ne .
Surface flav in glalrs prob- able exis ted vhich a s deeper than threshold depth of glrss operating s t r e s s .
Problem re l a t ed t o op t i ca l signal-to-noise r a t i o .
Phe intermit tent condition a n caused by a decrease in Laser output pover. The ms not determined.
Anondy
nings and master
None. All-up thermal/ Rpollo vacuum t e s t of each spat!- craf t would be repuired t o detect t h i s type of defect.
Glass doubler added. Apollo Other spacecraft glass applications revleved and a p F o p r i a t e correc- tiw measures taken where required.
Optical s ignal enhanced Apollo by increasing Lens apcr- ature and delet ing in- f rared f i l t e r . Optical noise reduced. Manual override of velocity/ a l t i t ude sensor provided.
Automatic pover compen- Apollo sat ion c i r c u i t added t o Apollo
adequate level . Relay which w a s source of EMI wan removed from remain-
faullmaintain pover output a t
25
26
27
2a
19
30
31
Panoramic camera'veloc- i t y l a l t i t u d e sensor d i d not provide proper con- t r o l for camera.
Laser al t imeter a l t i t u d da ta becaw intermit ten a f t e r revolution 24 and no a l t i t ude da t a vere o ta ined a i t e r r e w l u t i o n
138. pping cnuern exten- on and retract ion t i m r e longer than normal d camera would not r e ac t af ter 15th ( l a s t )
ray spectrometer ienced gain s h i f t emporary spectrum reference s h i f t .
ar surface d r i l l i n g
Penetration t o full
achieved. . Releasing bore stem
t h vi th bore stems
om drill adapter vas
Bore stem damaged
Core stem d i f f i cu l t ar first j o i n t .
remove from d r i l l e d
Core stem sections f f i c u l t t o separate.
Vehicle/ Equipcent IM-10
~ ~~~
LM-10
LM-lo
SIM
SIM
SIM
SIM
AJSEP
F-27
Miss11
poll0 r Indetermined.
: ah sh i f t caused by aging If photomultiplier tube in 3 a m n ray detector assembly h e t o h i@ cosmlc ray f lux rates. Zero shif t probably :aused by open or short withi pulse he i@t analyzer.
1. Reduced depth of f l u t e s Bore stem Jo in t s kpollo s t j o in t s caused binding of items. 3. Lunar soil did not hold Wrench provided t h a t Rpollo w r e stem stat ionary and core item wench did not fit bore items properly. ill adapter eliminated. :. Up-and-dm movement of Bore stem Jo in t s b.pollo kill separated first j o i n t . 3. Frict ion from compacted Mechanical n t r a c - kpollo aa te r i a l i n f lu t e s . on device provided.
C. Holding vise ma mounted iackvard on LRV pa l l e t . In- s t a l l a t ion drawing i n error .
References
MSC-05161
MSC-05161
MSC-05161
MSC-05161
MSC-05161 HSC-07230
YSC-05161 JSC-07954
KSC-05161
l6C-05161
KSC-05161
wc-05161
YSC-0x61
KX-05161
F- 28
Lunar sur face 16- cauera magazine J m d
Lunmr surface 7 0 4 camera stopped at end (
second EVA.
Uater v88 d i f f i c u l t t o ob ta in from i n s u i t d r i r i n g device.
Oxygen purge system an- t enna broke.
k osa lv :;0 . S t a t e z e n t
32
33
34
35
36
37
d
19
10
tl
12
13
Centra l s t a t i o n rear c u r t a i n r e t a l n e r remom lanyard broke.
Universal handling too: d id not lock in place suprathermal ion detec. t o r f i t t i n g .
C r o u n d - c o m d e d t e l e - v i s ion could not b e ell vated as u n i t approach( limits o f t r a v e l .
L u n a r c o m i c a t i o n s ri lay u n i t downlink signr l o s t after lunar modul, ascent .
eployment saddle vas d i f f i c u l t t o r e l e = e h ' o m vehic le .
a t t e r y 2 voltl- ter as inopera t ive .
m n t s t e e r i n g system ~ 1 ) i n o p e r a t i v e upon e h i c l e a c t i v a t i o n and ! wing f i r s t EVA.
Vehicle/ Equipmenl
a E P
ALSEP
GFE
CFE
CFE
GFE
CFE
GFE
CFE
IRV
LRV
LRV
180-pound t e s t .
,001.
llastomer c l u t c h fac ing ma- .erlal degraded under opera- Sng condi t ions . creased.
:u r ren t capac i ty of 7.5-am- ,ere LRV c i r c u i t b reaker vas legraded because of e l e v a t e d f o r t h e 7.5-ampere c i r - emperatures.
l o v over r id ing of t h e
c i r c u i t breaker i s by- passed when opera t ing i t h e e x t e r n a l power mode
'ape on camera caused m i s - a t i n g of magazines and cum- ra. Excessive manual ad- .ancement of f i lm deple ted 'i lm loops.
'VO s e t screws in d r i v e pin- on were s l i p p i n g on motor h a f t . used on set screws.
ev ices were not proper ly o s i t i o n e d wi th in t h e s u i t s .
nadvertent flexure and con- a c t .
unsui t ing . Antenna not deployed u n t i l after egress .
pr ing expanded end j-d fter no-load r e l e a s e . Knots n t i e d a l l w i n g cord t o re- r a c t i n t o housing.
e h i c l e n a t i l t e d , causing tress pre loading of vehic le / addle i n t e r f a c e .
None. I - o s e i b l e motor/gear t r a i n ssembly binding.
References
MSC-05161
MSC-05161
HSC-05161
MSC-05161
MSC-05161
MSC-05161
MSC-05161
WSC -05161
HSC-05161
HSC-05161
MSC-05161
MSC-05161 MSC-07230 MSC-07683
F- 29
APOLLO 2
0
1
i
1 !
I ~~~ ~~
Anomaly Vehicle! l o . I Sta tement Equipment Cause C o r r e c t i v e Action
c . B e l t s no t long
a . B e l t .hooks s l i p p e d through handholds when not i n u s e .
b. B e l t s snagged on G S connec tor when d i s p l a c e from proper stowage l o c t i o n s .
t o s e c u r e hooks t o out - board handholds e a s i l y .
44 Seat b e l t problems: I a . B e l t s no t s u f f i c i e n t l y
I st i f f . I b . B e l t s no t s u f f i c i e n t l y s t i f f . I c . Conformance of s u i t s t o s e a t e d p o s i t i o n was not a s c l o s e a s expec ted . I c . Overcenter t i L
en ing mechanism provide . 4
15
1 5
MSC-05161
MSC-05161
MSC-05161
Aqomaly
NO. I Sta tement
1 Water /g lycol tempera tur c o n t r o l c i r c u i t f a i l e d i n t h e au tomat ic mode.
2 SPS o x i d i z e r tank p r e s - s u r e measurement s h i f t e upward.
3 Computer i s s u e d gimbal l o c k i n d i c a t i o n when nc gimbal lock c o n p i t i o n e x i s t e d .
4 I n e r t i a l subsystem warn i n g s and coupl ing d a t a u n i t f a i l i n d i c a t i o n s occurred dur ing t r a n s - e a r t h f l i g h t .
5 Heat l e & i n t o hydrogen t a n k 3 was abnormally h igh e a r l y i n m i s s i o n .
6 Spacecraft d i d not r e - spond t o u p l i n k r e a l - t ime commands t w i c e .
a t e r system c h l o r i n a -
Pions. 8 a s s spec t rometer would
o t f u l l y r e t r a c t and i n a l l y s t a l l e d two- h i r d s o u t . F
Vehic le / Equipment
CSM-113
CSM-113
CSM-113
CSM-113
CSM-113
CSM-113
CSM-113
CSM-113
APOLLO 16 ~ ~~
Cause C o r r e c t i v e Action :4ission!
Crack i n output s i l i con-con- A l l remaining c o n t r o l - Apollo 1 t r o l l e d r e c t i f i e r used i n l e r s t e s t e d f o r forward Apollo 1 tempera ture c o n t r o l l e r caused breakdown v o l t a g e , al- r e c t i f i e r t o s e l f - g a t e on and though t e s t i s not con- remain on, r e s u l t i n g i n sec- c l u s i v e . If problem r e - ondary f a i l u r e of feedback o c c u r s , manual c o n t r o l c a p a c i t o r . is s a t i s f a c t o r y .
P r e s s u r e t r a n s d u c e r r e f e r - Transducers r e p l a c e d Apollo I ence c a v i t y leaked . a f t e r a l t i t u d e chamber
t e s t i n g vacuum checked p r i o r t o i n s t a l l a t i o n . Redundant d e v i c e s added f o r c r i t i c a l measurements on Apollo 1 7 and subse- quent s p a c e c r a f t .
Probably caused by vol tage F i l t e r added a c r o s s Apollo 2 t r a n s i e n t from c o n t a c t bounce p r i m r y of t ransformer of t h r u s t v e c t o r enable r e l a y i n d i g i t a l - t o - a n a l o g c o i -
v e r t e r p o r t i o n of cou- p l i n g d a t a u n i t .
Conductive contaminant i n None. No hazard t o Apollo 1 diode l o c a t e d i n f a i l d e t e c t crew i f d e f e c t r e o c c u r s c i r c u i t o f coupl ing d a t a u n i t i n t h i s and o t h e r ap- probably caused f a l s e i n d i c a - p l i c a t i o n s of diode i n t i o n s . guidance system.
Ambient a i r p robably leaked' i n t o i n s u l a t i o n vacuum an- nulus dur ing b o o s t .
Undetermined.
None. P r e f l i g h t pro- Apollo 1 cedures and i n s p e c t i o n Apollo 1 of t a n k s cons idered ade- qua te .
None, If c o n d i t i o n oc- Apollo S c u r s a g a i n , normal oper-.Apollo 1
l a t i o n can b e r e s t o r e d b: c y c l i n g up- te lemet ry COIL-
lmand r e s e t swi tch .
Tef lon b ladder w a s p robably Ampules checked for 4pOllo 1 pinched between b a s e p l a t e and s i d e w a l l of ampule. w a l l . Entrapped a i r r e -
b l a d d e r adhes ion t o s i d e -
moved t o reduce b ladder expans i o n .
I n i t i a l s talls were probably None. F a i l u r e cause caused by jamming of c a b l e i n n o t a p p l i c a b l e t o boom housing. F i n a l s tall Apollo 17 and subsequent was probably caused by inop- e r a t i v e motor due t o pre- vious s t a l l i n g wi th motor on.
4pollO 4pollO 1 1
s p a c e c r a f t .
References
MSC-07230 MSC-07598
MSC-07230
MSC-07230
MSC-07230 MSC-07571
MSC-07230
MSC-07230
JSC-07230
EC-07230
. , .
F- 30
Anomaly
NO. I Sta tement ~~
9 :amma r a y spec t rometer boom would not W l y r e t r a c t .
o O s c i l l a t i o n s o f s e r v i c e p r o p u l s i o n engine gimba yaw a c t u a t o r occur red when secondary servo loop was s e l e c t e d .
.1 Cabin f a n s made a loud "moaning" sound.
.2 S u i t p r e s s u r e t r a n s - ducer r e a d i n g was highe t h a n normal d u r i n g t r a n s e a r t h EVA.
t3 D i g i t a l event t imer in - d i c a t e d e r roneous t i m e .
14 Scanning t e l e s c o p e sha a x i s drove e r r a t i c a l l y
1 5 Two l i t h i u m hydroxide c a n i s t e r s s tuck i n s i d B when be ing removed.
16 High-gain an tenna c o d not b e acqui red f o r a i p roximate ly 1 112 hour whi le spacecraf t was j p a s s i v e thermal contrc and crew was a s l e e p .
17 Extending and l o c k i n g Y-Y s t r u t i n prepara- t i o n f o r e n t r y was d i - f i c u l t .
18 One of recovered main parachutes had numeral s m a l l h o l e s i n canopy
19 Water fg lycol found on command module f l o o r d u r i n g p o s t f l i g h t ope a t i o n s .
I
, h i c l e f iuipment
:SM-113
XM-113
CSM-113
CSM-113
CSM-113
CSM-113
CSM-113
CSM-113
CSM-111
CSM-11:
CSM-11
C o r r e c t i v e Action Missions Refkyences Cause.
a b l e probably jammed i n boom None. F a i l u r e cause p o l l o 1 5 MSC-07230 nus ing dur ing r e t r a c t i o n . 16
Apollo 17 and subsequent
changed t o provide s t r a '
no t a p p l i c a b l e t o
s p a c e c r a f t .
ness t o a c t u a t o r assemb
r e l i e f and prevent f l e x ing .
None.
1 pen i n r a t e feedback loop Routing of c a b l e har - p o l l o 16 MSC-07230 f secondary yaw servo sys- em. Open was p o s s i b l y a w e d by c a b l e f l e x i n g .
JI o b j e c t probably g o t i n t o .he fan and was l a t e r f r e e d .
and subsequent spacecra
, m a r d u s t p a r t i c l e was found Five-micron f i l t e r add- .n t r a n s d u c e r . It may have ed i n s u i t p r e s s u r e :aught i n air gap of v a r i a b l e s e n s e l i n e f o r Apollo 1 .e luc tance element.
: a r ing p o i n t s i n magnesium Uni t s v i s u a l l y inspec- p o l l o
r wear, p e r m i t t i n g i d l e r Skylab u n i t s t o b e mod- p o l l 0
, e e l . P a i n t p a r t i c l e s f r o m opening f o r o t h e r rewor .
roken socket s p r i n g i n t e l e - Apollo 17 harness in-
) t o r p l a t e s became e longated t e d f o r Apollo 17.
?ar t o r u b a g a i n s t number
m b e r wheel i n t e r f e r e d wi th roper count ing .
cope h a r n e s s connec tor .
p o l l o
p o l l 0
s p r i n g s . New h a r n e s s e s spec ted f o r broken
t o b e manufactured f o r Skylab spacecraf t . I i f i e d i f c a s e s r e q u i r e
MSC-07230
MSC-07230 MSC-07 573
a n i s t e r expansion from mois- Removal force s p e c i f i - p o l l o 16 MSC-07230 u r e bui ldup was g r e a t e r t h a n c a t i o n changed. F l i g h t o m a l dur ing solo f l i g h t be- procedures changed t o i ause s u i t c o n t r o l va lves s u r e t h a t s u i t c o n t r o l e r e p o s i t i o n e d t o full flow. v a l v e s a r e p o s i t i o n e d t . h a , t h e side-B f i t wits cabin flow f o r s o l o op- i g h t e r t h a n t h a t of s i d e A. e r a t i o n s .
Indetermined. P o s s i b l e l o g i c None. If problem was p o l l o 12 MSC-07230 , i r c u i t mal func t ion . i n e l e c t r o n i c s box , it p o l l o 1 3
has a low p r o b a b i l i t y p o l l o 1 4 of r e c u r r i n g . A ~ O , p o l l o 1 6 secondary u n i t can b e s e l e c t e d . I
I Cnsuff ic ien t c l e a r a n c e . None. AOH has i n f l i g h t Apollo 16 procedure f o r s t r u t ad- jus tment .
RCS yaw engines were f i r e d Command module landed Apollo a t 350 f e e t a l t i t u d e t o vent t rapped p r o p e l l a n t s and pres- and p r o p e l l a n t i s o l a - s u r e . Holes were caused by t i o n va lves c l o s e d . o x i d i z e r e x p e l l e d from plus yaw engines .
wi th RCS p r e s s u r i z e d Apollo 1 Apollo 1
MSC-07230
MSC-07230 MSC-07641
F i b e r under two O-ring s e a l s Bypass v a l v e , B-nut i n suit h e a t exchanger by- pass v a l v e .
connec t ions , and cabin f l o o r i n s p e c t e d f o r l e p r i o r t o launch.
- - Nc
20
-
21
22
23
24
25
26
27
20
29
30
-
I
i I
0 1
!
i
i
i I I
I I
I
0 j
- No.
20
-
21
22
23
24
?5
26
27
18
29
30
-
Anonalv
S t at ement
c rubber tank o f decon. amina t ion u n i t f a i l e d u r i n g p o s t f l i g h t deac i v a t i o n of r e a c t i o n C I
r o l system.
bo r e a c t i o n c o n t r o l ystem r e g u l a t o r i n l e t i l t e r s c r e e n s were de. ormed . 'henna1 c o a t i n g pee led May from a s c e n t s t a g e hermal s h i e l d pane ls .
our thermal s h i e l d s e r e t o r n l o o s e from a e n t s t a g e aft equipme ack.
-band s t e e r a b l e an- enna would n o t move i aw a x i s .
= a c t i o n c o n t r o l systen
eaked. helium r e g u l a t o r
%bin gas r e t u r n v a l v e p p a r e n t l y f a i l e d t o pen i n "automatic" s s i t i o n .
o n t r o l o f a s c e n t stage t t i t u d e l o s t a f t e r e t t i s o n .
bor t guidance system ut-of-plane e r r o r was a r g e r t h a n expec ted .
nd ica ted ascent engine hamber p r e s s u r e showec wo temporary r i s e s boye normal.
o m n d module t e l e - i s i o n camera monitor xt h o r i z o n t a l synchrt i z a t i o n t w i c e .
Vehic le / Equipment
GSE
CSM-113
LM-11
LM-11
LM-11
LM-11
LM-11
LM-11
LM-11
LM-11
GFE
F- 31
APOLLO 16
Cause
?apid o v e r p r e s s u r i z a t i o n of tank occurred because of i n - s u f f i c i e n t q u a n t i t y of neu- t r a l i z e r f o r t h e q u a n t i t y of 3 x i d i z e r .
F i l t e r element end caps were bulged by helium p r e s s u r e surge dur ing system a c t i v a - t i o n .
Coating was not compatible with t h e thermal condi t ions exper ienced ,
Probably caused by i n s u f f i c i e n t v e n t i n g of thermal b lanket dur ing e a r t h launch , and ascent engine exhaust en t e r i n g c a v i t y behind thermal s h i e l d s dur ing ascent from l u n a r s u r f a c e .
Stow l a t c h mechanism d i d not r e l e a s e an tenna . Exact caus unknown,
l o s t probably caused by con- ;amination in t roduced d u r i n g :omponent replacement and, iubsequent ly , swept i n t o r e g i l a t o r o u t l e t by backflow.
=robably caused by contamina .ion on i n l e t sc reen or on Clapper va lve .
Che most l i k e l y cause was an >pen c i r c u i t b reaker which i rovides 28 v o l t s t o t h e p r i nary p r e a m p l i f i e r s . It e i t h l i d not make c o n t a c t o r was i n a d v e r t e n t l y l e f t open.
Ihe most l i k e l y cause was :ontamination or an air bub- > l e i n t h e f l u i d between t h e jyro f l o a t and c a s e .
I n d i c a t i o n s caused by charac . e r i s t i c s of p r e s s u r e t r a n s - lucer .
:awed by e i t h e r an i n t e r m i t Lent c o n d i t i o n i n p r e c i s i o n ro l tage r e g u l a t o r c i r c u i t a s sembly i n low-voltage power ;upply, or s h i f t i n s t a b l e "ange of h o r i z o n t a l poten- Aometer s e t t i n g .
C o r r e c t i v e Action
Decontamination proce- aure changed. Cont ro l of procedure and paper - work formal ized . De- ac t iva t ion /Decontamina- t i o n Manager appoin ted .
None r e q u i r e d .
Coating was removed from Apollo 17 space- c r a f t because adequate thermal p r o t e c t i o n was provided by t a n k i n s u l t t i o n .
Thermal s h i e l d conf ig- u r a t i o n changed. Addi- t i o n a l v e n t i n g of t h e r . mal b l a n k e t s provided.
Exposed s o l d e r f i l l e t removed from stow l a t c t mechanism. I n s p e c t i o n and checkout procedure: improved. Wiring addec t o provide redundant pa ths through s a f e l a r m swi tch t o s o l d e r mel t i r elements.
Ua components r e p l a c e d lownstream of Apollo 17 ? e g u l a t o r s . Changes nade t o launch s i t e t e s ing t o e l i m i n a t e regula ;or backflow.
Pest added t o p r e f l i g h t :heckout of Apollo 17 spacecraf t .
Vone r e q u i r e d .
t b o r t s e n s o r assembly i n s t a l l e d i n Apollo 17 s p a c e c r a f t checked f o r 'ontamination and a i r Jubbles.
'lone r e q u i r e d .
Low-voltage power suppl r o l t a g e r e g u l a t o r s r e - placed on remaining f l i g h t u n i t s . Warm op- ; i m u m s e t t i n g marks ap- ? l i e d t o TV monitor c a s
4 i s s i c - ,pollo
1p0ll0
ip0 l lo
ipo l lo
\ p o l l o
pollo
p o l l o
p o l l o
po l lo
p o l l o
p o l l o
References
MSC-07230
MSC-07230 MSC-07640
MSC-07230
MSC-07230
MSC-07230
MSC-072 30
MSC-07230
MSC-07230
MS C-07 230
MSC-07230
MSC-07230 MSC-07489
". " I .
F- 32
Anomaly
0 . S t at ement -
3
4
5
5
7
0
9
IO
i l
42
43
Oxygen purge system an- t enna b roke .
Experimental gas lwa te r s e p a r a t o r was cracked and l eaked .
Wrist d i sconnec t s were ha rd t o r o t a t e a f t e r ex posu re t o lunar s u r f a c e environment.
Headset microphone boom t i p was loose .
Headset earphone opera- t i o n was i n t e r m i t t e n t .
R e t r a c t a b l e t e t h e r woul n o t f u l l y r e t r a c t .
P re s su re i n d i c a t e d by cuff gage was low dur- i n g t r a n s e a r t h EVA.
Ex t r aveh icu la r m o b i l i t j u n i t maintenance k i t expanded.
P res su re garment a s - sembly purge v a l v e p in came ou t on t h r e e occa- s i o n s .
Too l c a r r i e r f e l l o f f p o r t a b l e l i f e support system dur ing EVA prep r a t i o n s .
Lunar Module P i l o t ' s w a t c h ' c r y s t a l came ou t du r ing luna r s u r f a c e a t i v i t y .
Cable broke on hea t f l experiment.
One of fou r s t a g e s on a c t i v e se i smic expe r i - ment mortar package pa let d id n o t deploy,
44 Telemetry i n d i c a t i o n c a c t i v e se i smic expe r i - ment mortar box roll i was o f f - sca l e N g h ,
45 Cosmic r a y d e t e c t o r pane l shade d id no t f u l l y deploy and lan- yard broke.
i e h i c l e f Squipment
GFE
GFE
GFE
GFE
GFE
GFE
GFE
GFE
GFE
GFE
GFE
ALSEP
ALSEP
ALSEP
e
Lunar SUK
f a c e ex- periment
Cause Cor rec t ive Action Missions
henna i n a d v e r t e n t l y l e f t Spare antenna stowed on 4pol lo 1 5 istowed dur ing i n g r e s s , and l u n a r rove r f o r Apollo 4pOllo 16 .obably s t r u c k a scen t en- 17 . ne cover .
l i t was made fo r demonstra- None. Device no t flown 4pol lo 16 .on purposes and m a t e r i a l LS h i g h l y s u s c e p t i b l e t o .acking.
m a r d u s t got between s l i d - Ig su r faces .
on subsequent missions.
Rubber dus t covers add- Apollo 1 6 ed f o r Apollo 17.
I
? s u f f i c i e n t adhesive a p p l i e d Pull t e s t added t o as- ien t i p was i n s t a l l e d on s u r e adequate a t t a c h - : o u s t i c a l t u b e . ment.
Apollo le
l e c t r i c a l adap te r 21-pin None. m n e c t o r was probably no t ea t ed secu re ly .
p o l l o 1f I hread s e a l a n t on spoo l shaf t Un i t s t e s t e d f o r f r i c - Apollo 1: ncreased f r i c t i o n . t i o n bu i ldup p r i o r t o Apollo 1f
f l i g h t .
ontaminant may have tempo- None r e q u i r e d . Apollo l( a r i l y caused r e s i s t a n c e i n echanism movement, o r gage ay have been misread.
et-wipe packe t s expanded i n Some v a r i a t i o n i n ex- Apollo l( abin environment. pansion can b e expected.
Apollo 17 crew briefed. ,
i n was probably pu l l ed ou t Purge v a l v e assembly Apollo 11 y red app le on lanyard snag- modified by e l i m i n a t i n g ing on luna r rover l a p b e l t . b a r r e l a c t u a t o r s p r i n g
and shor t en ing l anya rd .
Pin p u l l f o r c e increasecApollo 1 from 5 l b t o between 10 and 20 l b .
,nap buckle r e l e a s e p in was . nadve r t en t ly pu l l ed .
iarpage of c r y s t a l from the r - None. t a l cyc l ing caused it to pop ,u t . OK crew s a f e t y .
Watch no t c r i t i - Apollo 1 c a l t o mission Success
Cibbon cab le became entangled Connector was modified y i th crewman's f e e t and was t o provide s t r a i n r e l i e f m l l e d loose a t c e n t r a l s t a - and g r e a t e r p u l l s t r e n g t h t i o n connector . f o r Apollo 17.
Release p i n was bent and None. Experiment .not Apollo 1 j ammed .
Apollo 1
scheduled f o r subsequent, mission.
Sensor c i r c u i t f a i l u r e . None. Experiment n o t Apollo 1 Other d a t a ind ica t ed that scheduled f o r subsequent alignment was s a t i s f a c t o r y . mission.
I n s u f f i c i e n t c l ea rance be- None. Experiment n o t Apollo tween s t a t i o n a r y b lockp la t e and movable t a r g e t p l a t e be- cause of p r o j e c t i n g screws.
scheduled f o r subsequent mission.
3eferences
3-07230
SC-07230
SC-07230
SC-07230
ISC-07230
ISC-07230
ISC-07230
1SC-07230
4%-07230
4SC-07230
MSC-07230
MSC-07230
MSC-07230
MSC-07230
MSC-07230
--
I
I.
F- 33
Cause
he most probable cause was reaking of t h e inne r gim- a1 p ivo t p i n s .
lethod of l a t c h i n g d i spense r idapter t o camera w a s inad- iqua te .
; c r e w s came l o o s e .
Cor rec t ive Act ion
P ivo t p i n s f o r t h e Apollo 1 7 gnomon w e r e given a d d i t i o n a l t e m - pe r ing and a t h i n f i l m of o i l was app l i ed t o p r o t e c t a g a i n s t cor ro- s i o n .
Adapter redes igned .
Apollo 17 d i spense r s i n spec ted t o a s s u r e proper s t a k i n g of screw!
Jnomaly
0. S ta tement
Improper bond m a t e r i a l used f o r Velcro hook pa tch . t aken s i n c e t h i s equip-
No c o r r e c t i v e a c i t o n
ment w a s no t scheduled f o r ano the r f l i g h t .
Lanyard loop w a s p robably Cable s i z e changed from not p rope r ly crimped t o 3/64 i n c h t o 1 /16 inch c a b l e . and p u l l t e s t e d .
Based on ground tests, mor ta r No c o r r e c t i v e a c t i o n assembly i s p i t ched up above taken a s t h e experiment normal 45” e l e v a t i o n or p i t c h was no t scheduled f o r sensor has f a i l e d . Most another miss ion . l i k e l y cause i s f a i l u r e i n p i t c h sensor c i r c u i t .
Unknown. (See Apollo 17 Openings i n gea r box i t e m 23. ) sea l ed w i t h pressure-
s e n s i t i v e t a p e . Excess l u b r i c a n t removed from d r i v e screw. Cover ove rear t r a n s f e r g e a r s re- des igned .
Undetermined. Poss ib l e cause Dr ive r a c k a l igned f o r w a s misalignment of d r i v e proper p in ion gear en- r ack and p in ion gear when as- gagement. sembly was f u l l y extended.
5
7
8
9
IO
i l
52
53
54
55
56
57
Apollo 17 laser module modified t o incorpora t f Q-switch bea r ings w i t h o i l - impregnated b a l l r f
t a i n e r s . High p u r i t y ‘ q u a r t z used i n f l a sh lan
V e r t i c a l s t a f f of gno- mon sepa ra t ed from l e g assembly.
I
Lies repea ted ly f e l l f f b racke t s on 70-mn ameras .
xumented sample bag i spense r suppor t r acke t came a p a r t .
ample c o l l e c t i o n bag ame loose from p o r t a b l i f e suppor t sygtem t o o arrier s e v e r a l t i m e s .
unar su r face f a r u l - r a v i o l e t camera a z i - u t h ad jus tment became i f f i c u l t .
e l c r o pa t ch came o f f added sample bags.
,oop came o f f lanyard o r pene t rometer stow- Ige. r e l e a s e p i n ,
c t i v e seismic exper i - bent p i t c h sensor in- l i ca ted o f f - sca l e h igh l f t e r launching t h i r d ;renade.
lapping camera ex tend/ .etract t i m e s were ab- iormally long .
lapping camera s t e l l a r Clare s h i e l d f a i l e d t o c e t r a c t .
,aser a l t ime te r ’ou tpu t legraded .
Panoramic camera au to- n a t i c exposure cont ro l ind ica t ed low l i g h t l e v e l s .
e h i c l e / quipment
lnar sur- c e ex- mriment
mar sur - i c e ex- x i m e n t
l n a r s u r - 8ce ex- zriment
m a r SUP
ace ex- e r iment
unar s u r - ace ex- e r iment
unar SUK-
a ce ex- er imen t
unar sur . ace ex- e r iment
ALSEP
S I M
S I M
S I M
S I M
APOLLO 2
I I
+ethod of a t tachment was in - adequate.
:rease i n azimuth r i n g bear - ing became s t i f f .
Bag hooks r edes igned .
No c o r r e c t i v e a c t i o n w a s t aken s i n c e t h i s experiment was n o t scheduled f o r ano the r f l i g h t .
Most probable cause of Apollc 1 5 and Apollo 16 f a i l u r e s was contaminat ion of o p t i c a l s u r f a c e s wi th in laser module by l u b r i c a n t from Q-switch bear ings .
added t o p r e f l i g h t test
i ss io i
0110 -
80110
,0110
,0110
,0110
p o l l o
po l lo
p o l l o
p o l l o p o l l o po l l a
p o l l c .pollc
.pollc ,pollc
,po l l<
References
ISC-07230
4SC-07230
MSC-07230
MSC-07230
MSC-07230
MSC-07230
MSC-07230
MSC-07230
MSC-05 161 MSC-07230 JSC-07954
MSC-07230 JSC-07954
MSC-05161 MSC-07230
MSC-07230
F- 34
AFOLLO 3
- No.
58 -
59
60
61
62
63
64
I
Anomaly
S ta tement
.aser altimeter photo- i u l t i p l i e r tube v o l t a g e ras errat ic .
l ine f rames of mapping :amera me t r i c photo- ;raphs overexposed.
fapping camera f i l m w a s : on tamha ted ,
l l e c t r i c a l system meter inomalies : I . Ba t t e ry 2 vo l tme te r ind ica ted o f f - sca l e low I , Bat t e ry 2 ampere- lour meter ind ica t ed I f f - sca l e low. :. Bat t e ry 1 and 2 tern i e r a t u r e meters i n d i c a t , f f - sca l e low.
t e a r s t e e r i n g inopera- :ive.
Vavigation system com- puted parameters d i d nc update.
Sca le debonded from p i t c h a t t i t u d e senso r .
Anomalv
No.
1 - Sta tement
occurred wi thout accom-- panying c a u t i o n and warning l i g h t s .
2 Miss ion . t imer was 15 seconds slow a t about 2 hours a f t e r l i f t - o f f .
3 Re t r ac t l i m i t sw i t ch on luna r sounder HF an- tenna boom 1 d i d n o t ac t u a t e
Vehicle/ Equipment
SIM
SI11
SIM
LRV
LRV
LRV
LRV
Veh ic l e / Equipment
CSM-114
CSM-114
CSM-114
Cause
Some anomalous v o l t a g e s prob- a b l y cuased by sun l igh t re- f l e c t i o n s . An i n t e r m i t t e n t cond i t ion could have been caused by c y c l i c thermal en- vironment of l una r o r b i t .
Noise v o l t a g e on power sup- p l i e d t o s h i f t r e g i s t e r o r genera ted by some i n t e r m i t - t e n t cond i t ion i n camera must have switched one o r more s t a g e s i n r e g i s t e r on o r o f f .
Most l i k e l y cause was r e s idue from manufacturing o r contam- i n a n t s in t roduced from some o u t s i d e sou rce .
Undetermined. I n t e r m i t t e n t cond i t ions must have e x i s t e d i n s e v e r a l mul t ip le -wire s p l i c e s ,
Open c i r c u i t may have oc- cur red i n hand c o n t r o l l e r po ten t iome te r , o r between poten t iometer wiper and sum- ming d iode ,
C i r c u i t b reaker and swi t ch conf igu ra t iqn was probably i n c o r r e c t .
The most probable cause w a s a f l aw i n t h e bonding.
APOLLO JJ
Cor rec t ive Act ion
00 c o r r e c t i v e a c t i o n taken because qua l i f i c a t i o n test r e s u l t s and ai lep tance tests were con s ide red adequate .
Vo c o r r e c t i v e a c t i o n gas taken because qua l - i f i c a t i o n tes t r e s u l t s snd acceptance tests a e r e cons idered adequats
qore thorough c l ean ing and i n s p e c t i o n proce- dures implemented.
No c o r r e c t i v e a c t i o n taken because cause of i n t e r m i t t e n t c o n d i t i o n s could no t be determined
[lo c o r r e c t i v e a c t i o n taken . Problem could not be f u r t h e r i s o l a t e d and e x i s t i n g des ign and t e s t i n g were cons idered adequate .
No c o r r e c t i v e a c t i o n r equ i r ed .
No c o r r e c t i v e a c t i o n r e q u i r e d .
l i s s i o n :
p o l l o 1
p o l l o 1
p o l l o I
,po l lo I
tpo l lo 1 ipo l lo 1
\ p o l l 0
\po l lo
References
MSC-07230
MSC-07230
MSC-07230
MSC-07230 MSC-07684
MSC-05161 MSC-07230 MSC-07683
MSC-07230
MSC-07230
Cause Cor rec t ive Act ion Miss ions References
I n t e r m i t t e n t ground i n pane l None r equ i r ed . Apollo 17 JSC-07904 2. C i r c u i t r y i s c u r r e n t l i m - i t e d so no hazard r e s u l t e d .
Not de te rmined .
Abnormal f r i c t i o n on- t h e l i m l t swi tch cam fo l lower arm, d e f e c t i v e l i m i t sw i t ch a c t u a t i n g mechanism sp r ing , misalignment of t h e an tenna t ape element s l o t , o r a m a l - f unc t ion i n t h e l i m i t sw i t ch assemblv.
None - v e h i c l e h a s re- dundant timers . JSC-07904
JSC-07904
i
7
10
11
-
Anomalv
S ta tement
unar sounder h igh f r e - uency an tenna boom 2 eployment was s lower han expec ted .
n t r y moni tor system cce lerometer n u l l b i a s h i f t e d .
h l o r i n e ampule leaked .
lapping camera plume ; h i e l d door f a i l e d t o : lose.
Jydrogen t anks 1 and 2 x e s s u r e ope ra t ing deal >and decreased i n au to natic h e a t e r mode.
Erroneous measurements t r ansmi t t ed by telemet
Water fg lycol tempera- t u r e c o n t r o l v a l v e f a i t o main ta in t h e evapo- r a t o r tempera ture .
Ba t t e ry 4 v o l t a g e rear i n g was lower than th; of b a t t e r y 3.
Vehi d e / Equipment
:SM-114
iM-114
jM-114
SM-114
SM-114
SM-114
SM-114
LM-12
APOLLO 2
Cause Cor rec t ive Act ion ~~~
)t determined. Increased None - device no t t o be id va ry ing loads i n a the r - flown on f u t u r e miss ion ilfvacuum environment a r e
xhanisms s e v e r a l t i m e s on x d l o .
mtamina t ion i n accelerom- None r equ i r ed . t e r o r open o r s h o r t c i r c u i t I t h e acce lerometer c o n t r o l
p e c u l i a r i t y experienced i n '
F K C U i t S .
l adder was no t completely Skylab and Apollo-Soyuz Dmpressed i n t h e ampule crews t r a i n e d t o prop- o r e . When i n j e c t o r was then e r l y compress t h e b lad- a t e d wi th the w a t e r p o r t , d e r be fo re mating i n j e c ack p res su re ballooned and t O K t o water p o r t . o r e the b l adde r .
o t determined. Increased None - dev ice no t t o bi nd vary ing loads i n a the r - flown on f u t u r e m i s - iallvacuum Cnvironment are a s i o n s . ' e c u l i a r i t y exper ienced i n iechanisms s e v e r a l times on g o l l o .
' robably contaminat ion i n t h e None r equ i r ed . Prob- iydrogen tank Rressure sen- l e m s of t h i s n a t u r e cai ; ing swi tch s t o p s reduced the be handled by manual c ; w i t c h ' s s h a f t t r a v e l t h a t t K 0 1 of t ank f a n s and educed the upper and lower h e a t e r c y c l e s . leadband p res su re sp read .
L f a i l u r e occurred somewhere A mating connec tor f o r .n t h e las t f o u r s t a g e s of t h e PCM package GSE co irogrammer counter A. I f t h e nec to r w i l l be c a r r i e d . a i l u r e had not become i n t e r - i n t h e Skylab and t h e i i t t e n t , au tomat ic counter ASTP s p a c e c r a f t . The iwitchover would not have oc- connec tor w i l l have an iurred and t h e a f f ec t ed meas- i n t e r n a l jumper t h a t irements would have been perm-grounds t h e proper p in inent ly l o s t . so t h a t t h e crew can
swi t ch t o t h e des i r ed programmer counter A o B .
; t i ck ing OCCUKS i n va lve gear None - manual va lve op : ra in a f t e r d r i v i n g hard e r a t i o n i s s a t i s f a c t o r * g a i n s t f u l l c losed s t o p PO- as shown dur ing Apollo s i t i o n . P i t c h c i r c l e s of two 16. :ear p a i r s i n t h e va lve gear r r a i n a r e sometimes no t tan- :ent. Causes con tac t ing t e e t t Co s l i d e r a t h e r t han r o l l . U s 0 some gear t r a i n s have dr! Lubricant sc raped of f t h e geai r e e t h i n t h e a r e a of c o n t a c t , Lausing h igh s l i d i n g f r i c t i o n .
Ba t t e ry 4 v o l t a g e reading w a s None - t h i s c i r c u i t r y no t a t r u e reading . The w i l l no t be flown on i
v o l t a g e measurement s i g n a l planned f u t u r e missior cond i t ione r has an inpu t re- s i s t i v e d i v i d e r network. A r e s i s t i v e inc rease of 1 per- c e n t i n t h i s network would account f o r t h e lower v o l t a g e of b a t t e r y 4 . Another pos- s i b i l i t y of t h i s type e x i s t s i n 'the zero-adjus t network.
s s i o n :
0110 1
0110 1
0110 1
,0110 :
10110
30110
p o l l 0
,po l lo
F- 35
References
SC-07904 SC-05161 ISC-07230
ISC-07904
ISC-07904
JSC-07904 JSC-05161 MSC-07230
JSC-07904
JSC-07904 JSC-07985
JSC-07904 MSC-07 230
JSC-07904
.. . . . -. . . , . ..
F- 36
Anomaly lo. S ta tement
!3 No ex t r aveh icu la r ac- t i v i t y warning tone i n Command Module P i l o t ' s communications c a r r i e r .
L4 Lunar s u r f a c e gravim- eter beam cannot be
15 Sur face e lectr ical p r o p e r t i e s r e c e i v e r tempera ture h igher t h a p red ic t ed .
16 Lunar e j e c t a and m e t e - o r i t e experiment tem- p e r a t u r e h i g h .
11 Cask dome removal was d i f f i c u l t .
Background n o i s e i n t h e luna r a tmospher ic composition experiment d a t a .
'chicle/ Quipment
LM-12
GFE
ALSEP
, m a r s u r race ex- ,eriment
ALSEP
ALSEP
ALSEP
WOLLO 2
Cause Cor rec t ive Act ion I
~~ ~
ould have been caused by None - t h i s equipment ontaminat ion of r e g u l a t o r A; i s not t o be used on
2.5-micron p a r t i c l e between f u t u r e s p a c e c r a f t . he r e g u l a t o r ( b a l l ) poppet nd t h e s e a t . Also p o s s i b l e , ut no t l i k e l y , t h e crew coulc cave inadve r t en t ly bumped t h e . e g u l a t o r handle .
l aming tone l o s s and l e f t , C r e w t r a i n i n g and pro- !arphone l o s s were caused by cedures r ev i sed t o re- wo w i r e l e a d s broken 114- f l e c t a ha rness conf ig- nch below t h e i r e x i t po in t u r a t i o n t h a t p reven t s 'rom t h e p o t t i n g of t h e f l e x . e l i e f a t t ached t o t h e lower ha rness . ?nd of t h e communications :arrier s p l i c e b lock .
Lathematical des ign e r r o r re- The beam h a s been ba l - ;u l ted i n t h e senso r mass anced and cen te red by $e ight be ing about 2 pe rcen t p a r t i a l cag ing of t h e l i g h t e r than t h e proper nomi- mass weight assembly. h a 1 weight f o r 1 /69 opera- Fur the r ana1ysi.s of d a t : ion. channels i s i n p rogres s
t o de te rmine i f free mode o s c i l l a t i o n s and g r a v i t y waves are being de tec t ed w i t h t h i s con- f i g u r a t i o n .
None - t h i s experiment i s not scheduled f o r a
t w i s t i n g of the wire
A dus t f i l m cover ing 10 per- cent of t h e o p t i c a l s o l a r r e f l e c t o r (n i i r ror ) on top of f u t u r e miss ion , howevei t h e r ece ive r could r e s u l t i n s i m i l a r bonding conf ig- the ind ica t ed degrada t ion of u r a t i o n s w i l l . r e q u i r e thermal c o n t r o l . Also , t h e s t r i n g e n t q u a l i t y con- thermal Kapton bag top cover f l a p s could no t be t i g h t l y c losed t o keep p u t dus t and s u n l i g h t . ' .
Erro r i n c a l c u l a t i n g thermal c o n t r o l conf igu ra t ion capa- j i l i t y f o r Apollo 17 s i te .
t r o l .
Ins t rument i s o p e r a t i n ; p rope r ly b u t is commani o f f each luna r day unt l i t s tempera ture c o o l s down aga in . Temperatux of ope ra t ion is be ing inc reased i n con t ro l l ec increments each luna r I u n t i l a l l owab le maximun i s reached .
Removal t o o l p i n s were n o t The dome was e a s i l y locked i n t o t h e recess i n the wedged of f t h e cask w i l
t h e hammer. No f u r t h e l dome. i n v e s t i g a t i o n w a s per- formed s i n c e t h e cask no t scheduled t o be f l i on f u t u r e miss ions .
Cause i s n o t known. The cond i t ion is st; ibl and has caused no l o s s of d a t a . No f u r t h e r ground tests a r e p lann s i n c e t h i s experiment w i l l no t be flown on f u t u r e miss ions .
- , ssions'
0110 17 -
80110 1 7
,0110 1;
p o l l o 1
p o l l o 1
p o l l o 1
.pol lo 1
-
References
ISC-07904
ISC-07904
JSC-07904
JSC-07904
JSC-07904
JSC-07904
JSC-07904
F- 37
~
C o r r e c t i v e Ac t ion
The o v e r r i d e c a p a b i l i t y was used f o r t h e remain- d e r of t h e mis s ion . T h i s l o c k s o u t t h e sen- s o r and s u b s t i t u t e s p re - set v o l t a g e s which COK-
r e sponds t o o r b i t a l t r a v e l rates f o r 55 and 60 m i l e a l t i t u d e s . Thi: w a s t h e last mis s ion f o r t h e panoramic camera an< no f u r t h e r i n v e s t i g a t i o r is n e c e s s a r y .
The f i l m w a s p r o p e r l y exposed showing t h a t n o t h i n g was r educ ing the l i g h t b e i n g t r a n s m i t t e d t o ttfe f i l m . The o n l y loss w a s t h e t e l e m e t r y i n d i c a t i o n t h a t confirms t h a t t h e l i g h t had been t r a n s m i t t e d . S ince t h i s was t h e last mis s ion f o r t h i s camera, no f u r t h e r a n a l y s i s i s necessa ry .
I
~ ~
Missioi
Apollo
Apollo
- No.
19 -
20
11
! 2
23
-
. lost l i k e l y , t h e gimbal d r i v e notor f a i l e d s i n c e t h e motor orushes a r e l i m i t e d l i f e items. Another p o s s i b i l i t y is f a i l u r e of t h e electrical A r c u i t r y t h a t p rov ides power I O t h e motor .
' robably a component f a i l u r e )r a s h o r t i n t he c i r c u i t v i r ing i n t6e r e f e r e n c e v o l t - ige O K t he minus 1 5 v o l t 'upply.
The behav io r w a s q u i t e s i m - i la? t o t h a t dui-ing t h e Apollo 1 5 and 1 6 mis s ions . Other anomalies i n t h e s c i e n - t L f i c i n s t rumen t module bay sugges t a common unknown fac - t o r . I n a l l c a s e s , some de- g r e e of s l i d i n g between m e t a l s u r f a c e s w a s r e q u i r e d . The f r i c t i o n between those s u r - f a c e s may have been s i g n i f i - c a n t l y i n c r e a s e d by t h e e f - fects of a ha rd vacuum i n space t h a t i s unob ta inab le i n grounc t e s t i n g .
Anomaly
S t a t ement
No c o r r e c t i v e a c t i o n Apollo was t aken s i n c e t h i s waE t h e last mis s ion f o r t h i s camera.
These were housekeeping Apollo measurements and were independent of s c i e n t i f i c d a t a c i r c u i t r y . S ince t h i s w a s t h e on ly mis s i cn f o r t h i s i n s t r u m e n t , no c o r r e c t i v e a c t i o n was taken.
S ince t h i s was t h e l a s t Apollo mis s ion f o r t h i s i n s t r u - ment , no c o r r e c t i v e ac- t i o n w a s t aken . However t h e g e n e r a l problem is be ing s t u d i e d f o r f u t u r e mis s ions a t Lewis Re- s e a r c h Cen te r .
,noramic camera ve- c i t y f a l t i t u d e senso r e r a t e d e r r a t i c a l l y .
ipping camera exposure ilse a b s e n t a t low g h t l e v e l s .
inoramic camera gim- 1 1 d r i v e f a i l e d d u r i n g . n a l pas s .
t r a v i o l e t spec trom- er t empera tu re m e a s - ement f a i l u r e s .
spping camera dep loy / : t r a c t times were ex- I s s i v e .
Veh ic l e / Equipment
SIM
S I M
S I M
S I M
S I M
Cause
i n a l y s i s i n d i c a t e s t h a t t h e ? r r a t i c o p e r a t i o n may have - e s u l t e d frdm a downward ; h i f t in t h e s c a l i n g of t h e sensor o u t p u t s i g n a l . T h i s # o d d most l i k e l y be caused 'y a f a i l u r e w i t h i n t h e sen- ;or head c i r c u i t r y .
Che l i g h t s e n s o r c i r c u i t r y zxperienced a t h r e s h o l d s h i f t . Th i s s h i f t could have >een t h e r e s u l t of a photo- i i o d e f a i l u r e OK a change i n the performance of t h e ampli- l i e r , t h e one-shot m u l t i v i - . r a t o r o r t h e c i r c u i t r y be- :ween t h e s e two e l emen t s ,
Re fe rences
JSC-07904
JSC-07904 MSC-05161 MSC-07230
JSC-07904
ISC-07904
MSC-05161 MSC-07230 JSC-07904 JSC-07954